CN107991676A - Troposphere error correction method of satellite-borne single-navigation-pass InSAR system - Google Patents
Troposphere error correction method of satellite-borne single-navigation-pass InSAR system Download PDFInfo
- Publication number
- CN107991676A CN107991676A CN201711250005.XA CN201711250005A CN107991676A CN 107991676 A CN107991676 A CN 107991676A CN 201711250005 A CN201711250005 A CN 201711250005A CN 107991676 A CN107991676 A CN 107991676A
- Authority
- CN
- China
- Prior art keywords
- mrow
- msubsup
- mover
- msub
- error
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
- G01S13/9021—SAR image post-processing techniques
- G01S13/9023—SAR image post-processing techniques combined with interferometric techniques
-
- 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
-
- 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
- G01S7/4004—Means for monitoring or calibrating of parts of a radar system
Abstract
The invention provides a troposphere error correction method of a satellite-borne single-navigation InSAR system. The technical scheme is as follows: firstly, calculating a two-dimensional measurement error introduced by a troposphere in a distance-height plane by utilizing a troposphere influence effect model of a satellite-borne single-navigation InSAR system, an auxiliary radar incident angle and a priori troposphere zenith delay; then, decomposing the two-dimensional error into a three-dimensional ground-fixed coordinate system for representation through projection transformation according to the spaceborne SAR imaging geometric model; and finally, correcting the troposphere error influence in the detected scene point by point. The method has high correction precision, can be used for directly processing the interference positioning result, and has simple and efficient operation process.
Description
Technical field
The invention belongs to the interleaving techniques field of space remote sensing and atmospheric effect, navigated InSAR for spaceborne list
The tropospheric error correction side of (Interferometric Synthetic Aperture Radar, interference synthetic aperture radar)
Method.
Background technology
Spaceborne list InSAR systems of navigating are single using a pair of the same area obtained under the different observation visual angle of main and auxiliary radar
The three-dimensional information of earth's surface is obtained depending on the interference phase difference inverting between complex pattern, the mapping task to global landform is completed and generates
High-precision DEM (Digital Elevation Model, digital elevation model).
Atmospheric effect is to restrict spaceborne list to navigate a key factor of InSAR system intervention measurement accuracy.Wherein, convection current
Layer is the bottom of air, connects with earth's surface downwards, extends upwardly to about at the 16km of earth's surface overhead, constituent contains a variety of
Gas (nitrogen, oxygen, carbon dioxide etc.) and steam, numerous weather phenomena occur in troposphere.The orbit altitude of satellite
Convection current layer height is above, tropospheric influence can be subject to when the electromagnetic wave of radar emission passes through troposphere, gives satellite-borne SAR figure
As introducing certain time delay and phase error, and then influence the performance of InSAR systems.Research shows that conventional convection layer is to spaceborne
The influence for InSAR systems of singly navigating up to several meters of magnitudes, must usually be corrected in high-precision interferometry.Therefore have
Necessity apply tropospheric radio propagation mechanism, proposes to correct for the navigated high-precision tropospheric error of InSAR systems of spaceborne list
Method.At present, it is not yet found that closing the related data of bearing calibration.
The content of the invention
The present invention in order to effectively solve the problems, such as spaceborne list navigated InSAR systems tropospheric error influence, it is proposed that Yi Zhongji
Navigated InSAR system tropospheric error bearing calibrations in the spaceborne list of priori tropospheric zenith delay.This method correction accuracy is high,
Processing procedure is relatively easy, navigates InSAR systems suitable for the spaceborne list under known priori tropospheric zenith delay distribution situation
Tropospheric error correction.
The present invention basic ideas be：First, navigated InSAR system troposphere influential effect models using spaceborne list, profit
With auxiliary radar incidence angle and priori tropospheric zenith delay, calculate the two-dimensional measurement that troposphere introduces in distance-height plane and miss
Difference；Then, according to Space-borne SAR Imaging geometrical model, by projective transformation, two-dimentional error is decomposed under three-dimensional body-fixed coordinate system
Represent；Finally, the tropospheric error that pointwise correction is tested in scene influences.
The technical scheme is that：
It is known at any time under the orbit coordinate A (x that navigated under the auxiliary star body-fixed coordinate system of InSAR systems of spaceborne listA, yA,
zA), auxiliary radar incidence angle θ, is tested the corresponding tropospheric zenith time delay τ of scenezenith；It is known to be influenced by tropospheric
Coordinate B (x of any point under body-fixed coordinate system in scene is tested afterwardsB, yB, zB), which determined by directly reading InSAR
Position result obtains.
It is B (x for coordinate in tested sceneB, yB, zB) arbitrary point, using following steps complete scene three-dimensional coordinate
Tropospheric error influences correction：
The first step：Navigated InSAR system troposphere influential effect models according to spaceborne list, and calculated distance-height
Horizontal measurement error and vertical survey error in plane.
According to auxiliary radar incidence angle θ tropospheric zenith delay τ corresponding with tested scenezenithTroposphere is calculated to spaceborne
The horizontal measurement error that InSAR systems of singly navigating introduceWith vertical survey error
In above formula, c represents the light velocity.
Second step：Two-dimensional measurement error pro is transformed to and is represented under three-dimensional body-fixed coordinate system.
First, vertical survey error is calculated using following formulaError vector under body-fixed coordinate system
Wherein xBC、yBCAnd zBCIt is expressed as：
Then, calculated level measurement errorError vector under under body-fixed coordinate system
In above formula, O is that coordinate of the earth's core under body-fixed coordinate system is (0,0,0), because A, B coordinate are it is known that vectorWithIt can ask.
Finally, the body-fixed coordinate system three-dimensional coordinate offset vector that troposphere introduces is calculated according to the following formula
3rd step：Obtain the three-dimensional body-fixed coordinate system coordinate for correcting and scene being tested after tropospheric error influences.
The body-fixed coordinate system three-dimensional coordinate offset vector introduced according to troposphereIt is B (x to coordinateB, yB, zB) appoint
Point calibration tropospheric error of anticipating influences, and the three-dimensional body-fixed coordinate system B'(x of measured point in scene is tested after being correctedB', yB', zB'),
Wherein xB'、yB'And zB'It is expressed as：
xB'=xB+xBE
yB'=yB+yBE
zB'=zB+zBE
Following technique effect can use to obtain using the present invention：
Navigated InSAR system tropospheric error bearing calibrations the present invention provides a kind of spaceborne list, this method is based on priori
Tropospheric zenith delay distribution, navigated InSAR system troposphere influential effect models using spaceborne list, by will theoretical two dimension
Measurement error, which is transformed under three-dimensional body-fixed coordinate system, represents that InSAR systems were tested the troposphere of scene, it can be achieved that spaceborne list navigates
Error accurately corrects point by point.The bearing calibration taken into full account spaceborne list navigated InSAR basic principle and tropospheric propagation effect
The space-variant answered, correction accuracy is high, and simply efficient available for directly processing interference positioning result, operating process.
Brief description of the drawings
Fig. 1 is the principle of the present invention flow diagram；
Fig. 2 is the radar system and troposphere basic parameter set in emulation；
Fig. 3 is 1 spatial distribution map of priori tropospheric zenith delay in emulation experiment；
Fig. 4 is the three dimensional effects error space distribution map that troposphere introduces InSAR positioning results in emulation experiment；
Fig. 5 be the embodiment of the present invention in spaceborne list navigated InSAR systems tropospheric error correct residual error experimental result picture.
Embodiment
Elaborate below in conjunction with the accompanying drawings with specific embodiment to the present invention.Wherein, the spaceborne list in embodiment navigated
InSAR systems and tested scene are using the method generation of emulation.Specific principle of simulation and flow refer to Min Wang,
Diannong Liang were published in IEEE International Geoscience and Remote equal to 2007
Article SBRAS-An Advanced Simulator of Spaceborne on Sensing Symposium.
Fig. 1 is the principle of the present invention flow diagram, and whole flow process is divided into three big steps.The first step, calculates distance-height and puts down
Troposphere horizontal measurement error and vertical survey error in face；Second step, using satellite-borne SAR geometrical relationship, by two-dimensional measurement
Error pro transforms to be represented under three-dimensional body-fixed coordinate system, and it is inclined to being tested the three-dimensional body-fixed coordinate system that scene introduces to obtain troposphere
Move；3rd step, point-by-point accurate correction are tested the measurement error that measured point is introduced by tropospheric zenith delay in scene, are corrected
Tropospheric error is tested the three-dimensional body-fixed coordinate system coordinate of measured point in scene after influencing.
Fig. 2 is the radar system and troposphere basic parameter set in emulation.Spaceborne list InSAR systems of navigating are operated in X
Wave band (radar signal centre frequency is 9.65GHz), it is residual in order to contrast the correction of the priori tropospheric zenith delay of different accuracy
Difference, the priori tropospheric zenith delay that two kinds of precision are respectively adopted in the embodiment of the present invention carry out tropospheric error correction experiment.
Wherein, priori tropospheric zenith delay 1 is at a time is tested the corresponding true tropospheric zenith delay of scene, in scene
For space-variant, zenith delay excursion is 2.27 meters to 2.54 meters；Priori tropospheric zenith delay 2 is experience tropospheric zenith
Delay, takes 2.3 meters of constant value.
Fig. 3 is 1 spatial distribution map of priori tropospheric zenith delay in emulation experiment.The sky of priori tropospheric zenith delay 1
Between coordinate grid it is identical with tested scene coordinate grid, it is 1117 that transverse axis, which represents distance to, pixel number, in figure, and the longitudinal axis represents orientation
It is 1446 to, pixel number, distance is to being 3km with orientation size.
Gray value represents the tropospheric zenith delay value in tested scene in figure, and gray scale gets over superficial and shows tropospheric zenith in figure
Length of delay is bigger.From figure 3, it can be seen that the troposphere distribution in tested scene is distributed close to real space troposphere.
Fig. 4 is the three dimensional effects error space distribution map that is introduced to InSAR positioning results of troposphere in emulation experiment, in figure
It is 1117 that transverse axis, which represents distance to, pixel number, and the longitudinal axis represents orientation, and pixel number is 1446, and distance is to equal with orientation size
For 3km.Figure (a), which represents X-direction troposphere under body-fixed coordinate system, influences error, and whole scene average is about -2.17 meters；Scheme (b)
Representing Y direction troposphere under body-fixed coordinate system influences error, and whole scene average is about -2.8 meters；Figure (c) represents body-fixed coordinate system
The lower Z-direction troposphere of system influences error, and whole scene average is about 0.51 meter.Gray value represents that troposphere influences error in figure
Size, Fig. 4 (a) and gray scale in (b) get over superficial and show that error influence is smaller, and gray scale, which is more deeply felt, in Fig. 4 (c) shows that error influence is smaller.
As seen from the figure, troposphere navigated spaceborne list error caused by InSAR systems influence it is very notable, usually up to several meters of magnitudes,
And more significant space-variant is presented.
Fig. 5 be the embodiment of the present invention in spaceborne list navigated InSAR systems tropospheric error correct residual error experimental result picture, figure
It is 1117 that middle transverse axis, which represents distance to, pixel number, and the longitudinal axis represents orientation, and pixel number is 1446, distance to orientation size
It is 3km.Gray value represents to be tested the residual values of tropospheric error correction in scene, figure after being corrected using the present invention in figure
5 (a), (c), (e) and gray scale in (f), which are more deeply felt, shows that correction residual error is smaller, and Fig. 5 (b) gets over superficial with gray scale in (d) and shows correction residual error
It is smaller.Wherein, Fig. 5 (a), (c) and (e) are respectively to use the three-dimensional correction that priori tropospheric zenith delay 1 obtains in Fig. 2 residual
Difference, the whole scene average of tropospheric correction residual error of body-fixed coordinate system X-axis, Y-axis and Z-direction respectively may be about 4.4,2.6 and
14.4mm, correction accuracy respectively may be about 0.20%, 0.09% and 2.82%, illustrate to work as the corresponding accurate convection current of known tested scene
Layer zenith delay carry out tropospheric error correction correction residual error is smaller, correction accuracy is higher.Fig. 5 (b), (d) and (f) are respectively
The three-dimensional correction residual error obtained using priori tropospheric zenith delay 2 in Fig. 2, pair of body-fixed coordinate system X-axis, Y-axis and Z-direction
The whole scene average of tropospheric correction residual error respectively may be about -85.2, -113.3 and 35.4mm, correction accuracy respectively may be about 3.93%,
4.04% and 6.94%, correction residual result has the characteristic of space-variant.Wherein, the calculation formula of correction accuracy is removed for correction residual error
Size is influenced with initial error.Test result indicates that, convection current is carried out using the priori tropospheric zenith delay of two kinds of precision above
Layer error correction, correction residual error is smaller, in the case of inaccurate known tropospheric zenith delay spatial distribution, using experience
2.3 meters of tropospheric zenith delay carries out the InSAR systems tropospheric error correction of navigating of spaceborne lists and also can obtain good correction knot
Fruit.Using the present invention can effectively correct tropospheric propagation navigated to spaceborne list InSAR systems positioning result introducing three-dimensional position
Offset, correction accuracy can meet the application demand of high-precision mapping.
Claims (1)
1. a kind of spaceborne list navigated, InSAR system tropospheric error bearing calibrations, InSAR refer to interference synthetic aperture radar,
Spaceborne list navigated orbit coordinate A (x of the auxiliary star under body-fixed coordinate system of InSAR systems under knowing at any timeA,yA,zA), it is auxiliary
Radar incidence angle θ；The corresponding tropospheric zenith time delay τ of tested scenezenith；Any point is in body-fixed coordinate system in tested scene
Coordinate B (x under systemB,yB,zB), it is characterised in that
It is B (x for coordinate in tested sceneB,yB,zB) arbitrary point, using following steps complete scene three-dimensional coordinate convection current
Layer error influences correction：
The first step：Calculate the horizontal measurement error and vertical survey error in distance-height plane；
Using following formula calculate troposphere navigated to spaceborne list InSAR systems introducing horizontal measurement errorMissed with vertical survey
Difference
<mrow>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>h</mi>
<mi>o</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
<mo>=</mo>
<msub>
<mi>c&tau;</mi>
<mrow>
<mi>z</mi>
<mi>e</mi>
<mi>n</mi>
<mi>i</mi>
<mi>t</mi>
<mi>h</mi>
</mrow>
</msub>
<mi>t</mi>
<mi>a</mi>
<mi>n</mi>
<mi>&theta;</mi>
</mrow>
<mrow>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>v</mi>
<mi>e</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
<mo>=</mo>
<msub>
<mi>c&tau;</mi>
<mrow>
<mi>z</mi>
<mi>e</mi>
<mi>n</mi>
<mi>i</mi>
<mi>t</mi>
<mi>h</mi>
</mrow>
</msub>
<msup>
<mi>tan</mi>
<mn>2</mn>
</msup>
<mi>&theta;</mi>
</mrow>
In above formula, c represents the light velocity；
Second step：Two-dimensional measurement error pro is transformed to and is represented under three-dimensional body-fixed coordinate system：
First, vertical survey error is calculated using following formulaError vector under body-fixed coordinate system
<mrow>
<msub>
<mi>x</mi>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
</msub>
<mo>=</mo>
<mo>-</mo>
<mfrac>
<msub>
<mi>x</mi>
<mi>B</mi>
</msub>
<msqrt>
<mrow>
<msubsup>
<mi>x</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>y</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>z</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
</mrow>
</msqrt>
</mfrac>
<mo>&CenterDot;</mo>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>v</mi>
<mi>e</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>y</mi>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
</msub>
<mo>=</mo>
<mo>-</mo>
<mfrac>
<msub>
<mi>y</mi>
<mi>B</mi>
</msub>
<msqrt>
<mrow>
<msubsup>
<mi>x</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>y</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>z</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
</mrow>
</msqrt>
</mfrac>
<mo>&CenterDot;</mo>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>v</mi>
<mi>e</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>z</mi>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
</msub>
<mo>=</mo>
<mo>-</mo>
<mfrac>
<msub>
<mi>z</mi>
<mi>B</mi>
</msub>
<msqrt>
<mrow>
<msubsup>
<mi>x</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>y</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>z</mi>
<mi>B</mi>
<mn>2</mn>
</msubsup>
</mrow>
</msqrt>
</mfrac>
<mo>&CenterDot;</mo>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>v</mi>
<mi>e</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
</mrow>
Then, calculated level measurement errorError vector under under body-fixed coordinate system
<mrow>
<mover>
<mrow>
<mi>B</mi>
<mi>D</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>=</mo>
<mfrac>
<mrow>
<mo>(</mo>
<mover>
<mrow>
<mi>O</mi>
<mi>A</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>&times;</mo>
<mover>
<mrow>
<mi>O</mi>
<mi>B</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>)</mo>
<mo>&times;</mo>
<mover>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
</mrow>
<mrow>
<mo>|</mo>
<mrow>
<mo>(</mo>
<mover>
<mrow>
<mi>O</mi>
<mi>A</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>&times;</mo>
<mover>
<mrow>
<mi>O</mi>
<mi>B</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>)</mo>
</mrow>
<mo>&times;</mo>
<mover>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>|</mo>
</mrow>
</mfrac>
<mo>&CenterDot;</mo>
<msubsup>
<mi>&Delta;x</mi>
<mrow>
<mi>h</mi>
<mi>o</mi>
<mi>r</mi>
</mrow>
<mrow>
<mi>t</mi>
<mi>r</mi>
<mi>o</mi>
<mi>p</mi>
</mrow>
</msubsup>
</mrow>
In above formula, O is that coordinate of the earth's core under body-fixed coordinate system is (0,0,0)；
Finally, the body-fixed coordinate system three-dimensional coordinate offset vector that troposphere introduces is calculated according to the following formula
<mrow>
<mover>
<mrow>
<mi>B</mi>
<mi>E</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>=</mo>
<mover>
<mrow>
<mi>B</mi>
<mi>C</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
<mo>+</mo>
<mover>
<mrow>
<mi>B</mi>
<mi>D</mi>
</mrow>
<mo>&RightArrow;</mo>
</mover>
</mrow>
3rd step：Correction tropospheric error is tested the three-dimensional body-fixed coordinate system coordinate of scene after influencing；
The three-dimensional body-fixed coordinate system B'(x that measured point in scene is tested after correcting is calculated using following formulaB',yB',zB')：
xB'=xB+xBE
yB'=yB+yBE
zB'=zB+zBE
Correct result.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711250005.XA CN107991676B (en) | 2017-12-01 | 2017-12-01 | Troposphere error correction method of satellite-borne single-navigation-pass InSAR system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711250005.XA CN107991676B (en) | 2017-12-01 | 2017-12-01 | Troposphere error correction method of satellite-borne single-navigation-pass InSAR system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107991676A true CN107991676A (en) | 2018-05-04 |
| CN107991676B CN107991676B (en) | 2019-09-13 |
Family
ID=62035042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711250005.XA Active CN107991676B (en) | 2017-12-01 | 2017-12-01 | Troposphere error correction method of satellite-borne single-navigation-pass InSAR system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107991676B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109471104A (en) * | 2018-11-15 | 2019-03-15 | 首都师范大学 | A method of obtaining earth's surface three-dimensional amount of movement from two parallel orbit SAR datas |
| CN109583132A (en) * | 2018-12-18 | 2019-04-05 | 中国人民解放军国防科技大学 | Hypersonic aircraft landing probability calculation method based on radar detection error |
| CN109782282A (en) * | 2019-03-13 | 2019-05-21 | 武汉大学 | A kind of time series InSAR analysis method of integrated troposphere atmospheric delay correction |
| CN111239736A (en) * | 2020-03-19 | 2020-06-05 | 中南大学 | Single-baseline-based surface elevation correction method, device, equipment and storage medium |
| CN112344847A (en) * | 2020-11-20 | 2021-02-09 | 中国有色金属长沙勘察设计研究院有限公司 | Ground-based synthetic aperture radar data noise reduction method |
| CN116859391A (en) * | 2023-09-05 | 2023-10-10 | 中国科学院空天信息创新研究院 | InSAR troposphere delay correction method based on high-frequency texture cross correlation |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004095055A8 (en) * | 2003-04-17 | 2005-03-03 | Secr Defence | Correction of troposphere induced errors in global positioning systems |
| CN101770027A (en) * | 2010-02-05 | 2010-07-07 | 河海大学 | Ground surface three-dimensional deformation monitoring method based on InSAR and GPS data fusion |
| CN102243300A (en) * | 2011-04-15 | 2011-11-16 | 中国人民解放军国防科学技术大学 | Method for radio frequency interference suppression and error correction of low-frequency synthetic aperture radar |
| CN103033833A (en) * | 2012-12-13 | 2013-04-10 | 中国航天科工信息技术研究院 | Method of correcting troposphere delaying errors |
| CN103364766B (en) * | 2012-04-01 | 2015-02-04 | 中国科学院电子学研究所 | External calibration method of satellite-borne interferometric synthetic aperture radar (InSAR) system |
| CN106600551A (en) * | 2016-12-03 | 2017-04-26 | 中国人民解放军国防科学技术大学 | High-precision geometry geometric correction method for large-scene spaceborne SAR image |
-
2017
- 2017-12-01 CN CN201711250005.XA patent/CN107991676B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004095055A8 (en) * | 2003-04-17 | 2005-03-03 | Secr Defence | Correction of troposphere induced errors in global positioning systems |
| CN101770027A (en) * | 2010-02-05 | 2010-07-07 | 河海大学 | Ground surface three-dimensional deformation monitoring method based on InSAR and GPS data fusion |
| CN102243300A (en) * | 2011-04-15 | 2011-11-16 | 中国人民解放军国防科学技术大学 | Method for radio frequency interference suppression and error correction of low-frequency synthetic aperture radar |
| CN103364766B (en) * | 2012-04-01 | 2015-02-04 | 中国科学院电子学研究所 | External calibration method of satellite-borne interferometric synthetic aperture radar (InSAR) system |
| CN103033833A (en) * | 2012-12-13 | 2013-04-10 | 中国航天科工信息技术研究院 | Method of correcting troposphere delaying errors |
| CN106600551A (en) * | 2016-12-03 | 2017-04-26 | 中国人民解放军国防科学技术大学 | High-precision geometry geometric correction method for large-scene spaceborne SAR image |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109471104A (en) * | 2018-11-15 | 2019-03-15 | 首都师范大学 | A method of obtaining earth's surface three-dimensional amount of movement from two parallel orbit SAR datas |
| CN109471104B (en) * | 2018-11-15 | 2020-08-04 | 首都师范大学 | Method for acquiring three-dimensional movement amount of earth surface from SAR data of two parallel tracks |
| CN109583132A (en) * | 2018-12-18 | 2019-04-05 | 中国人民解放军国防科技大学 | Hypersonic aircraft landing probability calculation method based on radar detection error |
| CN109583132B (en) * | 2018-12-18 | 2023-04-07 | 中国人民解放军国防科技大学 | Hypersonic aircraft landing probability calculation method based on radar detection error |
| CN109782282A (en) * | 2019-03-13 | 2019-05-21 | 武汉大学 | A kind of time series InSAR analysis method of integrated troposphere atmospheric delay correction |
| CN109782282B (en) * | 2019-03-13 | 2023-04-18 | 武汉大学 | Time series InSAR analysis method integrating troposphere atmospheric delay correction |
| CN111239736A (en) * | 2020-03-19 | 2020-06-05 | 中南大学 | Single-baseline-based surface elevation correction method, device, equipment and storage medium |
| CN112344847A (en) * | 2020-11-20 | 2021-02-09 | 中国有色金属长沙勘察设计研究院有限公司 | Ground-based synthetic aperture radar data noise reduction method |
| CN116859391A (en) * | 2023-09-05 | 2023-10-10 | 中国科学院空天信息创新研究院 | InSAR troposphere delay correction method based on high-frequency texture cross correlation |
| CN116859391B (en) * | 2023-09-05 | 2023-11-10 | 中国科学院空天信息创新研究院 | InSAR troposphere delay correction method based on high-frequency texture cross correlation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107991676B (en) | 2019-09-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107991676B (en) | Troposphere error correction method of satellite-borne single-navigation-pass InSAR system | |
| US20200103530A1 (en) | Method for extracting elevation control point with assistance of satellite laser altimetry data | |
| CN107367716B (en) | A kind of high-precision satellite-borne SAR geometric calibration method | |
| CN110058236B (en) | InSAR and GNSS weighting method oriented to three-dimensional surface deformation estimation | |
| CN109917356B (en) | Airborne laser scanning system error calibration method | |
| CN107272039B (en) | A kind of positioning survey attitude positioning method based on double antenna GPS | |
| CN106556822B (en) | Spaceborne Sliding spotlight SAR pointing accuracy Orbital detection method | |
| CN103674063B (en) | A kind of optical remote sensing camera geometric calibration method in-orbit | |
| CN102998690B (en) | Attitude angle direct resolving method based on global position system (GPS) carrier wave double-difference equation | |
| CN103323855B (en) | A kind of precision acquisition methods of baseline dynamic measurement system | |
| CN112305510B (en) | DEM matching-based synthetic aperture radar image geometric calibration method | |
| CN107202582A (en) | The in-orbit real time imagery navigation of fixed statellite and method for registering | |
| CN110907932B (en) | Distributed InSAR satellite height measurement precision influence factor analysis method and system | |
| CN107504981A (en) | A kind of attitude of satellite error correcting method and equipment based on laser-measured height data | |
| CN110031877B (en) | GRNN model-based regional NWP troposphere delay correction method | |
| CN102323571B (en) | Distribution method of satellite-borne dual-antenna SAR (Synthetic Aperture Radar) interferometric calibrator with comprehensive overall parameter | |
| CN113671505B (en) | Synthetic aperture radar three-dimensional positioning method based on system geometric error compensation | |
| CN106908770A (en) | The ground integrated emulation mode of high-resolution microwave imaging satellite star | |
| Liu et al. | Accurate mapping method for UAV photogrammetry without ground control points in the map projection frame | |
| CN103995260A (en) | Synthetic aperture radar SAR imaging method and device | |
| CN108562900B (en) | SAR image geometric registration method based on elevation correction | |
| CN105698766A (en) | Satellite image RFM model block adjustment method with orientation parameter precision information taken into consideration | |
| CN109239710A (en) | Acquisition methods and device, the computer readable storage medium of radar elevation information | |
| CN102147249B (en) | Method for precisely correcting satellite-borne optical linear array image based on linear characteristic | |
| CN111505608A (en) | Laser pointing on-orbit calibration method based on satellite-borne laser single-chip footprint image |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |