CN105353376B - A kind of spatial target posture inversion method based on ISAR images - Google Patents
A kind of spatial target posture inversion method based on ISAR images Download PDFInfo
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- CN105353376B CN105353376B CN201510824741.6A CN201510824741A CN105353376B CN 105353376 B CN105353376 B CN 105353376B CN 201510824741 A CN201510824741 A CN 201510824741A CN 105353376 B CN105353376 B CN 105353376B
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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
- G01S13/904—SAR modes
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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
- G01S13/904—SAR modes
- G01S13/9064—Inverse SAR [ISAR]
Abstract
A kind of spatial target posture inversion method based on ISAR images is disclosed, including：Observation moment ISAR image based on target obtains solar panel shaft length, main body shaft length and the main body direction of principal axis of target；In yaw angle ψ, pitching angle theta and roll angleIt is the first emulation main body direction of principal axis that target is obtained under the conditions of 0 °, the observation moment yaw angle ψ of target is determined according to the angle between main body direction of principal axis and the first emulation main body direction of principal axist；In ψ=ψt、Under the conditions of obtain the second emulation main body shaft length of target, the observation moment pitching angle theta of target is determined according to main body shaft length and the second emulation main body shaft lengtht；In ψ=ψt, θ=θt、Under the conditions of obtain the 3rd emulation solar panel shaft length of target, the observation moment roll angle of target is determined according to solar panel shaft length and the 3rd emulation solar panel shaft length.The present invention can obtain the quantitative values on spatial target posture, can accurately be finally inversed by yaw angle, the angle of pitch and the roll angle of target, so as to more directly understand the skyborne characteristics of motion of target.
Description
Technical field
The present invention relates to signal characteristic control technology field, more particularly to a kind of spatial target posture based on ISAR images
Inversion method.
Background technology
The background of related to the present invention is illustrated below, but these explanations might not constitute the existing of the present invention
Technology.
Space technology is widely used in after military field, and the military struggle of space grows in intensity, and it is to win to capture space power
IT-based warfare triumph precondition, then each military power of the world carry out the research of space weapon one after another.In order to realize pair
The strike of unfriendly target, is badly in need of the radar scattering characteristic of research unfriendly target.Space exploration turns into countries in the world competitively with identification
The hot research direction of development.
It needs to be determined that the track and Classification and Identification characteristic parameter of satellite and a large amount of space junks during Space Target Surveillance,
Such as quality, structure, posture, function, further to be distinguished to the country origin of target, working condition, action in the air, mission
Not.Therefore in the urgent need to development space target radar identification technology, the various features information obtained according to radar extracts feature ginseng
Number, differentiates with reference to the feature samples storehouse set up to target.
Satellite has different actions in normal course of operation, for example, adjust its solar panel, antenna, remote sensing
Device, sensing of celestial body etc., while can also carry out certain orbit adjusting, these actions will all cause the attitude of satellite and radar observation
The change at visual angle, very big difficulty is caused to target identification, therefore should be incited somebody to action first according to prior information and radar ISAR images
The gesture recognition of target is come out, and support is provided for the identification such as object construction type.
The content of the invention
It is an object of the invention to propose that main body axle and the dimension information of sun board shaft are to mesh in a kind of utilization ISAR images
The algorithm that attitude angle carries out inverting is marked, the attitude angle of target in three axial directions can be relatively accurately finally inversed by, be space mesh
Mark posture, structure, type identification etc. and technical support is provided.
According to the spatial target posture inversion method based on ISAR images of the present invention, including：
S1, the observation moment ISAR image based on target obtain the axial characteristic value of target, and the axial characteristic value includes：
Solar panel shaft length lTC, main body shaft length lZCWith main body direction of principal axis；
S2, in yaw angle ψ, pitching angle theta and roll angleIt is the first emulation ISAR images that target is obtained under the conditions of 0 °,
Determine the first emulation main body direction of principal axis of target in the first emulation ISAR images；According to the main body direction of principal axis and the first emulation master
Angle between body axis direction determines the observation moment yaw angle ψ of targett；
S3, in ψ=ψt、Under the conditions of obtain target second emulation ISAR images, determine the second emulation ISAR
Second emulation main body shaft length of target in image；Target is determined according to the main body shaft length and the second emulation main body shaft length
Observation moment pitching angle thetat；
S4, in ψ=ψt, θ=θt、Under the conditions of obtain target the 3rd emulation ISAR images, determine the 3rd emulation
3rd emulation solar panel shaft length of target in ISAR images；According to the solar panel shaft length and the 3rd emulation solar panel axial length
Degree determines the observation moment roll angle of target；
Wherein, the observation moment ISAR image, the first emulation ISAR images, the second emulation ISAR images and the 3rd are imitative
True ISAR images are image of the target in radar observation coordinate system.
Preferably, the axial characteristic value of acquisition target described in step S1 is specially：
Choose at least two width ISAR images of the target in [t- Δs t, t+ Δ t] time range；
For each width at least two width ISAR images, the axial characteristic information of target is obtained；
The axial characteristic value of target is used as using the average value of at least axial characteristic information of two width ISAR images；
Wherein, t is the observation moment, and Δ t is default time range；The axial characteristic information refers to the solar panel of target
Axial length angle value, main body axial length angle value and main body axle are pointed to.
Preferably, further comprise before step S1：
Geocentric coordinate system, orbital coordinate system and target body coordinate system are set up, by orbital coordinate system by target subject axle
With Coordinate Conversion of the sun board shaft in target body coordinate system into geocentric coordinate system；
Radar fix system and radar observation coordinate system are set up, target subject axle and sun board shaft are existed by radar fix system
Coordinate in geocentric coordinate system is gone in radar observation coordinate system.
It is preferably based on Randon shift theories and obtains the main body axle and sun board shaft of target in geocentric coordinate system and radar
Coordinate in observation coordinate system.
Preferably, geocentric coordinate system, orbital coordinate system, target body coordinate system, radar fix system and radar observation coordinate
Met between system：
In formula, RobThe transition matrix of target body coordinate system, R are tied to for orbit coordinatedoTrack is tied to for geocentric coordinates to sit
Mark the transition matrix of system, RdRThe transition matrix of radar fix system, R are tied to for geocentric coordinatesRCRadar observation is tied to for radar fix
The transition matrix of coordinate system；Long, lati are respectively the longitude and latitude of radar observation station location, and ω, f, i, Ω, u are respectively
Target argument of perigee, true anomaly, orbit inclination angle, right ascension of ascending node and track angle in the orbital tracking at observation moment, and u
=ω+f.
Preferably, solar panel shaft length, the first emulation solar panel shaft length, the second emulation solar panel shaft length and the 3rd
The determination method of solar panel shaft length referred in emulation solar panel shaft length is：
Obtain first coordinate value of the sun two end points of board shaft in target body coordinate system；First coordinate value is changed into
The second coordinate value in radar observation coordinate system；Solar panel shaft length is determined according to the second coordinate value；
Main body shaft length, the first emulation main body shaft length, the second emulation main body shaft length and the 3rd emulation main body axial length
The determination method of the main body shaft length referred in degree is：
Obtain threeth coordinate value of main body two end points of axle in target body coordinate system；3rd coordinate value is changed into thunder
Take things philosophically the 4-coordinate value surveyed in coordinate system；Solar panel shaft length is determined according to 4-coordinate value.
Preferably, the observation moment yaw angle ψ of target described in step S2tMeet following relation：
ψt=φC-φS, wherein,
In formula, φCIt is to observe the folder in moment ISAR image between the main body axle and radar observation coordinate system Z axis of target
Angle, φSIt is the angle between the main body axle of target in the first emulation ISAR images and radar observation coordinate system Z axis；xC1、zC1Respectively
Be in observation moment ISAR image on target subject axle any point in X-axis and the coordinate value of Z axis.
Preferably, the observation moment pitching angle theta of target described in step S3tMeet following relation：
In formula, l 'ZSIt is the main body shaft length of target in the second emulation ISAR images.
Preferably, the observation moment roll angle of target described in step S4Meet following relation：
In formula, l "TSIt is the solar panel shaft length of target in the 3rd emulation ISAR images.
According to the spatial target posture inversion method based on ISAR images of the present invention, including：During observation based on target
The axial characteristic value that ISAR images obtain target is carved, the axial characteristic value includes：Solar panel shaft length, main body shaft length and master
Body axis direction；In yaw angle ψ, pitching angle theta and roll angleIt is the first emulation ISAR images that target is obtained under the conditions of 0 °, really
First emulation main body direction of principal axis of target in fixed first emulation ISAR images；According to main body direction of principal axis and the first emulation main body axle side
Angle between determines the observation moment yaw angle ψ of targett；In ψ=ψt、Under the conditions of obtain target second
ISAR images are emulated, the second emulation main body shaft length of target in the second emulation ISAR images is determined；According to main body shaft length and
Second emulation main body shaft length determines the observation moment pitching angle theta of targett；In ψ=ψt, θ=θt、Under the conditions of obtain target
The 3rd emulation ISAR images, determine the 3rd emulation ISAR images in target the 3rd emulation solar panel shaft length；According to the sun
Board shaft length and the 3rd emulation solar panel shaft length determine the observation moment roll angle of target.The present invention is no longer limited to space
The qualitative analysis of targeted attitude judges, but can obtain the quantitative values on spatial target posture, can be more accurately anti-
Yaw angle, the angle of pitch and the roll angle of target in three axial directions are performed, so as to more directly understand target in the air
The characteristics of motion.
Brief description of the drawings
By the embodiment part of offer referring to the drawings, the features and advantages of the present invention will become more
It is readily appreciated that, in the accompanying drawings：
Fig. 1 is the schematic flow sheet for showing the spatial target posture inversion method based on ISAR images according to the present invention；
When Fig. 2 is the observation for the target for showing the spatial target posture inversion method based on ISAR images according to the present invention
Carve the schematic diagram of ISAR images；
Fig. 3 is to show to imitate according to the first of the target of the spatial target posture inversion method based on ISAR images of the invention
The schematic diagram of true ISAR images.
Embodiment
The illustrative embodiments to the present invention are described in detail with reference to the accompanying drawings.Illustrative embodiments are retouched
State merely for the sake of demonstration purpose, and be definitely not to the present invention and its application or the limitation of usage.
ISAR in the present invention is Inverse Synthetic Aperture Radar, i.e. ISAR.Partially
Boat angle refer to the main body axle of target local level projection and target orbital coordinate system X-axis angle；The angle of pitch is
The angle that feeling the pulse with the finger-tip target main body axle is projected with main body axle in local level；Roll angle refers to the sun board shaft and solar panel of target
Angle of the axle in local level.
Fig. 1 shows the schematic flow sheet of the spatial target posture inversion method based on ISAR images according to the present invention.
In step sl, the observation moment ISAR image for being primarily based on target obtains the axial characteristic value of target.Observe moment ISAR figure
It seem the image that feeling the pulse with the finger-tip is marked in radar observation coordinate system.The axial characteristic value that the present invention is referred to includes：Solar panel shaft length lTC、
Main body shaft length lZCWith main body direction of principal axis.Fig. 2 shows the schematic diagram of the observation moment ISAR image according to the target of the present invention,
In figure, d1、d2Respectively two end points of target subject axle, d3、d4Respectively two end points of target sun board shaft, point ORFor thunder
Take things philosophically origin, the O for surveying coordinate systemRXCPFor the X-axis of radar observation coordinate system, ORZCPFor the Z axis of radar observation coordinate system, target
Intersection point d between sun board shaft and main body axle0(not shown in Fig. 2) and point OROverlap, φCIt is mesh in observation moment ISAR image
Angle between target main body axle and radar observation coordinate system Z axis.
The situation of error is easily produced in view of the axial characteristic value extracted from single width observation moment ISAR image, according to
The axial characteristic value of acquisition target is specially in the preferred embodiments of the present invention, step S1：
Choose at least two width ISAR images of the target in [t- Δs t, t+ Δ t] time range；
For each width in this at least two width ISAR images, the axial characteristic information of target is obtained；
Using this at least the axial characteristic information of two width ISAR images average value as target axial characteristic value；
Wherein, t is the observation moment, and Δ t is default time range；Axial characteristic information refers to the solar panel axial length of target
Angle value, main body axial length angle value and main body axle are pointed to.
In order to obtain coordinate of the target in radar observation coordinate system, so according to coordinate value determine target sun board shaft and
The size and main body axle of main body axle are pointed to, and may further include before step S1：
Geocentric coordinate system, orbital coordinate system and target body coordinate system are set up, by orbital coordinate system by target subject axle
With Coordinate Conversion of the sun board shaft in target body coordinate system into geocentric coordinate system；
Radar fix system and radar observation coordinate system are set up, target subject axle and sun board shaft are existed by radar fix system
Coordinate Conversion in geocentric coordinate system is into radar observation coordinate system.
According to a preferred embodiment of the invention, the main body axle and sun board shaft for obtaining target based on Randon shift theories exist
Coordinate in geocentric coordinate system and radar observation coordinate system.Preferably, geocentric coordinate system, orbital coordinate system, target body coordinate
Met between system, radar fix system and radar observation coordinate system：
In formula, RobThe transition matrix of target body coordinate system, R are tied to for orbit coordinatedoTrack is tied to for geocentric coordinates to sit
Mark the transition matrix of system, RdRThe transition matrix of radar fix system, R are tied to for geocentric coordinatesRCRadar observation is tied to for radar fix
The transition matrix of coordinate system；Long, lati are respectively the longitude and latitude of radar observation station location, and ω, f, i, Ω, u are respectively
Target argument of perigee, true anomaly, orbit inclination angle, right ascension of ascending node and track angle in the orbital tracking at observation moment, and u
=ω+f.
Assuming that length of the main body axle of target in target body coordinate system is lZ, target main body axle target body sit
Length in mark system is lT, then point d0、d1、d2、d3、d4Coordinate in target body coordinate system is respectively：
Wherein | x1|+|x2|=lZ、|y1|+|y2|=lT。
According to the method described above will point d0、d1、d2、d3、d4Coordinate Conversion in target body coordinate system is sat to radar observation
In mark system, then：
Point d0Coordinate in radar observation coordinate system is：
Point d1Coordinate in radar observation coordinate system is：
Point d2Coordinate in radar observation coordinate system is：
Point d3Coordinate in radar observation coordinate system is：
Point d4Coordinate in radar observation coordinate system is：
S2, in yaw angle ψ, pitching angle theta and roll angleIt is the first emulation ISAR images that target is obtained under the conditions of 0 °.
First emulation ISAR images refer to image of the target in radar observation coordinate system.Determine target in the first emulation ISAR images
First emulation main body direction of principal axis, then determines target according to the angle between main body direction of principal axis and the first emulation main body direction of principal axis
Observe moment yaw angle ψt。
Fig. 3 shows the schematic diagram of the first emulation ISAR images of the target according to the present invention, in figure, d1、d2Respectively mesh
Mark two end points of main body axle, d3、d4Respectively two end points of target sun board shaft, point ORFor the original of radar observation coordinate system
Point, ORXCPFor the X-axis of radar observation coordinate system, ORZCPFor the Z axis of radar observation coordinate system, sun board shaft and the main body axle of target
Between intersection point d0With point OROverlap, φCIt is to observe the main body axle of target and radar observation coordinate system Z axis in moment ISAR image
Between angle.
S3, in ψ=ψt、Under the conditions of obtain target second emulation ISAR images.Second emulation ISAR images
Refer to image of the target in radar observation coordinate system.Determine the second emulation main body axial length of target in the second emulation ISAR images
Degree, then determines the observation moment pitching angle theta of target according to main body shaft length and the second emulation main body shaft lengtht。
S4, in ψ=ψt, θ=θt、Under the conditions of obtain target the 3rd emulation ISAR images.3rd emulation ISAR figures
It seem the image that feeling the pulse with the finger-tip is marked in radar observation coordinate system.Determine the 3rd emulation solar panel of target in the 3rd emulation ISAR images
Shaft length, then determines the observation moment roll angle of target according to solar panel shaft length and the 3rd emulation solar panel shaft length；
Solar panel shaft length, the first emulation solar panel shaft length, the second emulation solar panel shaft length and the 3rd emulation are too
The solar panel shaft length referred in positive board shaft length can be determined by the following method：The sun two end points of board shaft are obtained in target
The first coordinate value in body coordinate system；The second coordinate value that first coordinate value is changed into radar observation coordinate system；Foundation
Second coordinate value determines solar panel shaft length.
Main body shaft length, the first emulation main body shaft length, the second emulation main body shaft length and the 3rd emulation main body axial length
The main body shaft length referred in degree can be determined by the following method：Main body two end points of axle are obtained in target body coordinate system
The 3rd coordinate value；The 4-coordinate value that 3rd coordinate value is changed into radar observation coordinate system；It is true according to 4-coordinate value
Determine solar panel shaft length.
Preferably, in step S2 target observation moment yaw angle ψtMeet following relation：
ψt=φC-φS, wherein,
In formula, φCIt is to observe the folder in moment ISAR image between the main body axle and radar observation coordinate system Z axis of target
Angle, φSIt is the angle between the main body axle of target in the first emulation ISAR images and radar observation coordinate system Z axis；xC1、zC1Respectively
Be in observation moment ISAR image on target subject axle any point in X-axis and the coordinate value of Z axis.
Preferably, in step S3 target observation moment pitching angle thetatMeet following relation：
In formula, l 'ZSIt is the main body shaft length of target in the second emulation ISAR images.
Preferably, in step S4 target observation moment roll angleMeet following relation：
In formula, l "TSIt is the solar panel shaft length of target in the 3rd emulation ISAR images.
Compared with prior art, the present invention is no longer limited to the qualitative analysis judgement to spatial target posture, but can
The quantitative values on spatial target posture are obtained, target yaw angle in three axial directions can be more accurately finally inversed by, bow
The elevation angle and roll angle, so as to more directly understand the skyborne characteristics of motion of target.
Although with reference to illustrative embodiments, invention has been described, but it is to be understood that the present invention does not limit to
The embodiment that Yu Wenzhong is described in detail and shown, in the case of without departing from claims limited range, this
Art personnel can make various changes to the illustrative embodiments.
Claims (6)
1. a kind of spatial target posture inversion method based on ISAR images, it is characterised in that including：
S1, the observation moment ISAR image based on target obtain the axial characteristic value of target, and the axial characteristic value includes：The sun
Board shaft length lTC, main body shaft length lZCWith main body direction of principal axis；
S2, in yaw angle ψ, pitching angle theta and roll angleIt is the first emulation ISAR images that target is obtained under the conditions of 0 °, it is determined that
First emulation main body direction of principal axis of target in first emulation ISAR images；According to the main body direction of principal axis and the first emulation main body axle
Angle between direction determines the observation moment yaw angle ψ of targett；
S3, in ψ=ψt、Under the conditions of obtain target second emulation ISAR images, determine the second emulation ISAR images
Second emulation main body shaft length of middle target；The sight of target is determined according to the main body shaft length and the second emulation main body shaft length
Survey moment pitching angle thetat；
S4, in ψ=ψt, θ=θt、Under the conditions of obtain target the 3rd emulation ISAR images, determine the 3rd emulation ISAR figure
The 3rd emulation solar panel shaft length of target as in；Determined according to the solar panel shaft length and the 3rd emulation solar panel shaft length
The observation moment roll angle of target；
Wherein, the observation moment ISAR image, the first emulation ISAR images, the second emulation ISAR images and the 3rd emulation
ISAR images are image of the target in radar observation coordinate system；
Wherein, the observation moment yaw angle ψ of target described in step S2tMeet following relation：
ψt=φC-φS, wherein,
In formula, φCIt is to observe angle, the φ in moment ISAR image between the main body axle and radar observation coordinate system Z axis of targetS
It is the angle between the main body axle of target in the first emulation ISAR images and radar observation coordinate system Z axis；xC1、zC1Respectively see
Any point is surveyed in moment ISAR image on target subject axle in X-axis and the coordinate value of Z axis；
The observation moment pitching angle theta of target described in step S3tMeet following relation：
In formula, l 'ZSIt is the main body shaft length of target in the second emulation ISAR images；
The observation moment roll angle of target described in step S4Meet following relation：
In formula, l "TSIt is the solar panel shaft length of target in the 3rd emulation ISAR images.
2. spatial target posture inversion method as claimed in claim 1, wherein, the axially special of target is obtained described in step S1
Value indicative is specially：
Choose at least two width ISAR images of the target in [t- Δs t, t+ Δ t] time range；
For each width at least two width ISAR images, the axial characteristic information of target is obtained；
The axial characteristic value of target is used as using the average value of at least axial characteristic information of two width ISAR images；
Wherein, t is the observation moment, and Δ t is default time range；The axial characteristic information refers to the solar panel axial length of target
Angle value, main body axial length angle value and main body axle are pointed to.
3. spatial target posture inversion method as claimed in claim 2, wherein, further comprise before step S1：
Geocentric coordinate system, orbital coordinate system and target body coordinate system are set up, by orbital coordinate system by target subject axle and too
Coordinate Conversion of the positive board shaft in target body coordinate system is into geocentric coordinate system；
Radar fix system and radar observation coordinate system are set up, by radar fix system by target subject axle and sun board shaft in the earth's core
Coordinate in coordinate system is gone in radar observation coordinate system.
4. spatial target posture inversion method as claimed in claim 3, wherein, target is obtained based on Randon shift theories
The coordinate of main body axle and sun board shaft in geocentric coordinate system and radar observation coordinate system.
5. spatial target posture inversion method as claimed in claim 4, wherein, geocentric coordinate system, orbital coordinate system, target sheet
Met between body coordinate system, radar fix system and radar observation coordinate system：
In formula, RobThe transition matrix of target body coordinate system, R are tied to for orbit coordinatedoOrbital coordinate system is tied to for geocentric coordinates
Transition matrix, RdRThe transition matrix of radar fix system, R are tied to for geocentric coordinatesRCRadar observation coordinate is tied to for radar fix
The transition matrix of system；Long, lati are respectively the longitude and latitude of radar observation station location, and ω, f, i, Ω, u are respectively target
Argument of perigee, true anomaly, orbit inclination angle, right ascension of ascending node and track angle in the orbital tracking at observation moment, and u=ω
+f。
6. spatial target posture inversion method as claimed in claim 5, wherein, solar panel shaft length, the first emulation solar panel
The determination of the solar panel shaft length referred in shaft length, the second emulation solar panel shaft length and the 3rd emulation solar panel shaft length
Method is：
Obtain first coordinate value of the sun two end points of board shaft in target body coordinate system；First coordinate value is changed into radar
The second coordinate value in observation coordinate system；Solar panel shaft length is determined according to the second coordinate value；
In main body shaft length, the first emulation main body shaft length, the second emulation main body shaft length and the 3rd emulation main body shaft length
The determination method of the main body shaft length referred to is：
Obtain threeth coordinate value of main body two end points of axle in target body coordinate system；3rd coordinate value is changed into radar to see
The 4-coordinate value surveyed in coordinate system；Solar panel shaft length is determined according to 4-coordinate value.
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| CN108680165B (en) * | 2018-05-04 | 2020-11-27 | 中国人民解放军63920部队 | Target aircraft attitude determination method and device based on optical image |
| CN112949555B (en) * | 2021-03-17 | 2023-03-24 | 西安电子科技大学 | Spatial target ISAR image classification method based on target prior information |
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| CN103616685B (en) * | 2013-12-04 | 2015-10-28 | 西安电子科技大学 | Based on the ISAR image geometry calibrating method of characteristics of image |
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