CN101846740A - Satellite-loaded SAR specified latitude area echo simulation method - Google Patents
Satellite-loaded SAR specified latitude area echo simulation method Download PDFInfo
- Publication number
- CN101846740A CN101846740A CN 201010179060 CN201010179060A CN101846740A CN 101846740 A CN101846740 A CN 101846740A CN 201010179060 CN201010179060 CN 201010179060 CN 201010179060 A CN201010179060 A CN 201010179060A CN 101846740 A CN101846740 A CN 101846740A
- Authority
- CN
- China
- Prior art keywords
- satellite
- angle
- echo simulation
- point
- equation
- 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
Images
Landscapes
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention discloses a satellite-loaded SAR specified latitude area echo simulation method, which comprises the following steps of: 1, performing spatial geometry relationship modeling on the satellite-loaded SAR; 2, acquiring satellite-loaded SAR echo simulation parameters through the given wave level parameter table; 3, acquiring a geocentric angle and a middle parameter K; 4, acquiring an angle gamma 1, an angle gamma 2, an ascending node argument u, a real argument of periapsis f, an eccentric angle E and an average argument of periapsis phi; 5, determining the initial time t1 of the echo simulation; 6, determining the finish time t2 of the echo simulation; and 7, performing the satellite-loaded SAR echo simulation according to the initial time t1 and the finish time t2 of the echo simulation. The satellite-loaded SAR specified latitude area echo simulation method has the advantages of high precision, strong practicality, low redundancy of the acquired simulation data, high intuition, and the like.
Description
Technical field
The present invention relates to a kind of satellite-loaded SAR specified latitude area echo simulation method, belong to the signal Processing field.
Background technology
Satellite-borne synthetic aperture radar (Synthetic Aperture Radar, SAR) system has gone through the development of decades, has obtained huge achievement, and its achievement is widely used in military and civilian.And all Spaceborne SAR System all be unable to do without echo simulation in development process, all need a large amount of echo simulation data sources such as signal processing algorithm research, testing performance index, hardware-in-the-loop simulation and other various experiments, so the satellite-borne SAR echo simulation is being brought into play indispensable vital role in the development process of Spaceborne SAR System.
The satellite-borne SAR echo simulation has very strong purpose, especially is embodied in to utilize the echo simulation data to test, utilize the echo simulation data that the imaging processing system is tested to the SAR system and utilize the echo simulation data to cooperate aspects such as various test experiments.Therefore the satellite-borne SAR echo simulation method requires to have the characteristics of dirigibility and accuracy, especially be embodied in requirement and can finish various specified latitude areas efficiently, accurately and carry out echoed signal emulation, because all need the echo simulation signal of various specified latitude areas such as experiments such as imaging performance index test, target localization tests.
After having determined track six roots of sensation number and visual angle, what latitude scope satellite beams is radiated in is determined the zero hour and the finish time by emulation, after the emulation moment, scope was determined, then the latitude scope that the wave beam irradiation area is covered in the simulation process had also just been determined.In traditional satellite-borne SAR echo simulation method, the emulation zero hour and the finish time are with the not directly contact of observed latitude scope, flying speed is carried out guestimate to the sub-satellite point latitude at most via satellite, and then the latitude scope that irradiation area covered of estimation wave beam roughly, and the error of this estimation is bigger, can not satisfy the simulation requirements to specified latitude area.In other words, traditional method is by simulation time scope decision observation area latitude scope, and the practical application great majority are inverse process, promptly wish to decide the simulation time scope by the observation area latitude scope.But because the mathematics of inverse process is found the solution very difficult, therefore method commonly used at present is to enlarge the simulation time scope to comprise the latitude scope of appointment to guarantee the observation area latitude scope, or repeatedly the initial moment and the finish time are adjusted to satisfy the observation to specified latitude area, but no matter be the sort of method, all additive decrementation a large amount of calculation resources.
Therefore will realize the echo simulation of satellite-loaded SAR specified latitude area, key is to be determined the starting and ending moment of emulation by the scope of specified latitude area, and then realizes the echo simulation of specified latitude area.
Summary of the invention
The objective of the invention is at satellite-borne SAR emulation can't realize to specified latitude area carry out efficiently, accurate echo simulation, a kind of satellite-loaded SAR specified latitude area echo simulation method has been proposed, can determine the initial moment and the finish time of satellite-borne SAR echo simulation fast, so realize to specified latitude area carry out efficiently, echo simulation accurately.
A kind of satellite-loaded SAR specified latitude area echo simulation method of the present invention comprises following step:
Step 1: satellite-borne SAR is carried out the space geometry relationship modeling;
Step 2: obtain satellite-borne SAR echo simulation parameter by given ripple position parameter list;
Step 3: obtain geocentric angle
With intermediate parameters K;
Step 4: obtain angle γ
1, angle γ
2, ascending node argument u, very near heart angle f, eccentric angle E and average near heart angle φ;
Step 5: determine the initial moment t of echo simulation
1
Step 6: determine the echo simulation t finish time
2
Step 7: according to the initial moment t of echo simulation
1With the echo simulation t finish time
2, carry out the satellite-borne SAR echo simulation.
The invention has the advantages that:
(1) precision height.Model used in the present invention is accurate, therefore can accurately obtain the echo simulation moment under the different latitude, and then can obtain the echoed signal of specified latitude area.
(2) practical.The present invention has very strong practicality, utilizes the present invention can satisfy in the satellite-borne SAR development process various experiments to the heavy demand of echo simulate signal under the specified latitude scope.
(3) efficient height.Do not relate to any calculation procedure consuming time in the method for the invention, especially do not need to enlarge emulation scope constantly, or constantly adjust the starting and ending moment of emulation, therefore have characteristics of high efficiency.
(4) the emulated data redundancy of obtaining is little.Utilization is according to observation area latitude variation range, the corresponding initial moment and the finish time of obtaining emulation, only need only echo simulation being carried out in the observation area, so data redundancy is little, also helps the processing of follow-up data.
(5) intuitive is good.Under traditional emulation mode, simulation time and observation area latitude relation is that the star ground coordinate transformation relation by complexity is described, and our bright relation with this complexity is described by model space geometric, has good intuitive.
Description of drawings
Fig. 1 is a schematic flow sheet of the present invention;
Fig. 2 is a satellite-borne SAR model space geometric synoptic diagram in the step 1 of the present invention;
Fig. 3 is a satellite beams visual angle floor map in the step 3 of the present invention;
Fig. 4 is Track of Sub-Satellite Point and an antenna beam aiming point track perspective view in the step 3 of the present invention;
Fig. 5 is in the embodiment of the invention during satellite uplink, actual observation zone latitude error change curve;
Fig. 6 is when satellite is descending in the embodiment of the invention, actual observation zone latitude error change curve.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention is a kind of satellite-loaded SAR specified latitude area echo simulation method, and flow process comprises following step as shown in Figure 1:
Step 1: satellite-borne SAR is carried out the space geometry relationship modeling;
As shown in Figure 2, thick dashed line is represented satellite orbit among the figure, satellite S is positioned on the satellite orbit, the beam center of satellite S and earth surface intersect at the P point, the P point is a position wave beam aiming point, 3 of satellite S, P point and the earth's core O have constituted a triangle, and the line of satellite S and the earth's core O and earth surface meet at the E point, and the E point is a substar; Arctic P through the earth
NThe warp and the equator of ordering with P intersect at the A point, through the arctic P of the earth
NThe warp and the equator of ordering with E intersect at the B point; Ascending node is C, and the perigee is K;
The track of substar E forms sub-satellite track DE, and DE is the ball great circle, is beam scanning locus of points D ' P through the P point curve parallel with sub-satellite track DE, D, D ' on same warp, arctic P
NWith a D, great circle of D ' formation, intersect at a F with the equator;
Wherein:
1) ∠ POA=L is intersection point (be referred to as wave beam aiming point) the pairing angle of latitude of wave beam with earth surface.
2) ∠ PSO=β is the antenna beam downwards angle of visibility.
3) ∠ COK=ω is an argument of perigee.
4) ∠ FOD=i is an orbit inclination.
5)
Be geocentric angle.
6) ∠ EOC=u is the ascending node argument.
Step 2: obtain satellite-borne SAR echo simulation parameter by given ripple position parameter list;
Obtain satellite semi-major axis a by given ripple position parameter list, orbit inclination i, orbital eccentricity e, the angle of depression, perigee ω, time of pericenter passage τ, observed object zone latitude variation range L
1～L
2, antenna beam downwards angle of visibility β, earth mean radius R, earth gravitational field gravitational constant μ.
Step 3: obtain geocentric angle
With intermediate parameters K;
As shown in Figure 3, obtain geocentric angle at a S, E, P, O in 4 determined planes
As shown in Equation (1):
As shown in Figure 4, Track of Sub-Satellite Point is two parallel circles with antenna beam aiming point track, and wherein Track of Sub-Satellite Point is the ball great circle, P '
NO is vertical with DO, and P '
NO and earth surface intersect at a P '
N, D, D ', P
N, P '
NOn a ball great circle, the vertical P ' of O ' D '
NO is in an O ', and then intermediate parameters K is as shown in Equation (2):
Step 4: obtain angle γ
1, angle γ
2, ascending node argument u, very near heart angle f, eccentric angle E and average near heart angle φ;
If angle γ
1=∠ P
NO ' P, angle γ
1As shown in Equation (3):
If angle γ
2=∠ D ' O ' P, angle γ
2As shown in Equation (4):
Ascending node argument u is as shown in Equation (5):
Very closely heart angle f is as shown in Equation (6):
f＝u-ω (6)
Eccentric angle E is as shown in Equation (7):
Average near heart angle φ is as shown in Equation (8):
φ＝E-e·sinE (8)
Step 5: determine the initial moment t of echo simulation
1
The initial moment t of echo simulation
1As shown in Equation (9):
Step 6: determine the echo simulation t finish time
2
With the latitude L in the step 2
2Bring in the step 4, will obtain latitude L
2The time ascending node argument u, formula (9) that average near heart angle φ brings step 5 in, obtain the echo simulation t finish time
2
Step 7: according to the initial moment t of echo simulation
1With the echo simulation t finish time
2, carry out the satellite-borne SAR echo simulation.
Obtaining the initial moment t of echo simulation
1With the echo simulation t finish time
2After, carry out the subsequent operation of echo simulation according to six transition matrixes of star ground coordinate.The echo simulation data of obtaining echo then are used for aspects such as SAR system testing, imaging processing system testing and algorithm research, especially finish the various system performance testings of specified latitude area.
It is up setting satellite among embodiment: the embodiment 1, uses the present invention and carries out the emulation of satellite-borne SAR ripple, specifically comprises following step:
Step 1: satellite-borne SAR is carried out the space geometry relationship modeling;
Geometric Modeling as shown in Figure 1.
Step 2: obtain satellite-borne SAR echo simulation parameter by given ripple position parameter list;
Satellite semi-major axis a=6887315.0m, orbit inclination i=97.0deg, orbital eccentricity e=0.0011, the angle of depression, perigee ω=0.0deg, time of pericenter passage τ=0.0s, target area latitude variation range L
1=10deg (north latitude 10 degree), L
2=20deg (north latitude 20 degree), antenna beam downwards angle of visibility β=30deg, earth mean radius R=6371140.0m, earth gravitational field gravitational constant μ=3.986013e14;
Step 3: obtain geocentric angle
With intermediate parameters K;
Through type (1) obtains
Through type (2) obtains K=0.995.
Step 4: obtain angle ∠ P
NO ' P, angle ∠ D ' O ' P, ascending node argument u, very near heart angle f, eccentric angle E and average near heart angle φ;
Through type (3) obtains γ
1=80.270deg; Through type (4) obtains γ
2=80.252deg; Through type (5) obtains u=9.748deg; Through type (6) obtains f=9.748deg; Through type (7) obtains E=9.738deg; Through type (8) obtains φ=9.727deg.
Step 5: determine the initial moment t of echo simulation
1
Through type (9) obtains t
1=153.694s.
Step 6: determine the echo simulation t finish time
2
With the latitude L in the step 2
2Bring in the step 4, will obtain latitude L
2The time ascending node argument u, formula (9) that average near heart angle φ brings step 5 in, obtain the echo simulation t finish time
2=233.141s.
Step 7: according to the initial moment t of echo simulation
1With the echo simulation t finish time
2, carry out the satellite-borne SAR echo simulation.
By the present invention the different latitude regional extent is obtained the emulation moment in the satellite-borne SAR echo simulation, consider that simultaneously there is certain inclination angle in the SAR satellite orbit, some high latitude zone be the irradiation less than, therefore choose north latitude 0 degree～north latitude 60 degree among the embodiment 2, obtain satellite uplink and descending result.Table 1 has provided simulation parameter, and table 2 has provided simulation result.
Table 1 simulation parameter
Table 2 simulation result
The satellite-borne SAR echo simulation is carried out in emulation according to table 2 constantly, during satellite uplink, actual observation zone latitude error change curve as shown in Figure 5, when satellite is descending, actual observation zone latitude error change curve as shown in Figure 6, by among Fig. 5 and Fig. 6 as can be seen, no matter satellite is up or descending, carry out echo simulation constantly according to the emulation that the method for the invention is obtained, ratio error is very little mutually with specifying the irradiation area latitude scope for the actual irradiation area latitude scope of finally obtaining, can ignore in actual applications, the method of the invention is without any interative computation, efficient is very high, can satisfy specifying the demand of observation area latitude emulation, has brought into play important effect in practical engineering application.
Claims (1)
1. a satellite-loaded SAR specified latitude area echo simulation method is characterized in that, comprises following step:
Step 1: satellite-borne SAR is carried out the space geometry relationship modeling;
Satellite S is positioned on the satellite orbit, and the beam center of satellite S and earth surface intersect at the P point, and the P point is a position wave beam aiming point, 3 of satellite S, P point and the earth's core O have constituted a triangle, the line of satellite S and the earth's core O and earth surface meet at the E point, and the E point is a substar, through the arctic P of the earth
NThe warp and the equator of ordering with P intersect at the A point, through the arctic P of the earth
NThe warp and the equator of ordering with E intersect at the B point; Ascending node is C, and the perigee is K;
The track of substar E forms sub-satellite track DE, and DE is the ball great circle, is beam scanning locus of points D ' P through the P point curve parallel with sub-satellite track DE, D, D ' on same warp, arctic P
NWith a D, great circle of D ' formation, intersect at a F with the equator;
Wherein:
1) ∠ POA=L is the intersection point of wave beam with earth surface, i.e. the pairing angle of latitude of wave beam aiming point;
2) ∠ PSO=β is the antenna beam downwards angle of visibility;
3) ∠ COK=ω is an argument of perigee;
4) ∠ FOD=i is an orbit inclination;
5)
Be geocentric angle;
6) ∠ EOC=u is the ascending node argument;
Step 2: obtain satellite-borne SAR echo simulation parameter by given ripple position parameter list;
Obtain satellite semi-major axis a by given ripple position parameter list, orbit inclination i, orbital eccentricity e, the angle of depression, perigee ω, time of pericenter passage τ, observed object zone latitude variation range L
1～L
2, antenna beam downwards angle of visibility β, earth mean radius R, earth gravitational field gravitational constant μ;
Step 3: obtain geocentric angle
With intermediate parameters K;
Obtain geocentric angle at a S, E, P, O in 4 determined planes
As shown in Equation (1):
Set P '
NO is vertical with DO, and P '
NO and earth surface intersect at a P '
N, D, D ', P
N, P '
NOn a ball great circle, the vertical P ' of O ' D '
NO is in an O ', and then intermediate parameters K is as shown in Equation (2):
Step 4: obtain angle γ
1, angle γ
2, ascending node argument u, very near heart angle f, eccentric angle E and average near heart angle φ; If angle γ
1=∠ P
NO ' P, angle γ
1As shown in Equation (3):
If angle γ
2=∠ D ' O ' P, angle γ
2As shown in Equation (4):
Ascending node argument u is as shown in Equation (5):
Very closely heart angle f is as shown in Equation (6):
f＝u-ω (6)
Eccentric angle E is as shown in Equation (7):
Average near heart angle φ is as shown in Equation (8):
φ＝E-e·sinE (8)
Step 5: determine the initial moment t of echo simulation
1
The initial moment t of echo simulation
1As shown in Equation (9):
Step 6: determine the echo simulation t finish time
2
Latitude L2 in the step 2 is brought in the step 4, will obtain latitude L
2The time ascending node argument u, formula (9) that average near heart angle φ brings step 5 in, obtain the echo simulation t finish time
2
Step 7: according to the initial moment t of echo simulation
1With the echo simulation t finish time
2, carry out the satellite-borne SAR echo simulation;
Obtaining the initial moment t of echo simulation
1With the echo simulation t finish time
2After, carry out the subsequent operation of echo simulation according to six transition matrixes of star ground coordinate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101790606A CN101846740B (en) | 2010-05-17 | 2010-05-17 | Satellite-loaded SAR specified latitude area echo simulation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101790606A CN101846740B (en) | 2010-05-17 | 2010-05-17 | Satellite-loaded SAR specified latitude area echo simulation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101846740A true CN101846740A (en) | 2010-09-29 |
| CN101846740B CN101846740B (en) | 2011-04-27 |
Family
ID=42771420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101790606A Expired - Fee Related CN101846740B (en) | 2010-05-17 | 2010-05-17 | Satellite-loaded SAR specified latitude area echo simulation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101846740B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102331576A (en) * | 2011-07-28 | 2012-01-25 | 北京航空航天大学 | Method for acquiring aiming point of SAR beam bunching work mode |
| CN102466799A (en) * | 2010-10-29 | 2012-05-23 | 中国科学院电子学研究所 | Method for simulating interference SAR (Synthetic Aperture Radar) echo data based on POS (Posture) motion data |
| CN102879768A (en) * | 2012-09-14 | 2013-01-16 | 北京航空航天大学 | Satellite-borne synthetic aperture radar (SAR) high-fidelity echo simulation method based on steady-state radar cross section (RCS) |
| CN103558592A (en) * | 2013-10-08 | 2014-02-05 | 北京航空航天大学 | Satellite-borne SAR echo data simulation method based on MPI parallel computing |
| CN103576148A (en) * | 2012-08-07 | 2014-02-12 | 中国科学院电子学研究所 | Method for simulating satellite-borne SAR range ambiguity noise image |
| CN109444881A (en) * | 2018-10-23 | 2019-03-08 | 中国电子科技集团公司第三十八研究所 | A kind of secondary surface layer detection radar substar pulse precise positioning method |
| CN109782280A (en) * | 2019-03-06 | 2019-05-21 | 中国科学院电子学研究所 | Based on high rail SAR antenna distance in calibration satellite to directional diagram measuring method |
| CN110275140A (en) * | 2019-06-19 | 2019-09-24 | 西安电子科技大学 | Satellite-borne SAR beam sweeping method based on parabola antenna |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6919839B1 (en) * | 2004-11-09 | 2005-07-19 | Harris Corporation | Synthetic aperture radar (SAR) compensating for ionospheric distortion based upon measurement of the group delay, and associated methods |
| CN1808172A (en) * | 2005-01-20 | 2006-07-26 | 中国科学院电子学研究所 | Original echo generation method for airborne Interference synthetic aperture radar |
| CN101281249A (en) * | 2008-05-20 | 2008-10-08 | 北京航空航天大学 | Method for modeling target dispersion characteristic of high resolution synthetic aperture radar |
-
2010
- 2010-05-17 CN CN2010101790606A patent/CN101846740B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6919839B1 (en) * | 2004-11-09 | 2005-07-19 | Harris Corporation | Synthetic aperture radar (SAR) compensating for ionospheric distortion based upon measurement of the group delay, and associated methods |
| CN1808172A (en) * | 2005-01-20 | 2006-07-26 | 中国科学院电子学研究所 | Original echo generation method for airborne Interference synthetic aperture radar |
| CN101281249A (en) * | 2008-05-20 | 2008-10-08 | 北京航空航天大学 | Method for modeling target dispersion characteristic of high resolution synthetic aperture radar |
Non-Patent Citations (5)
| Title |
|---|
| 《仪器仪表学报》 20090630 李卓 等 顶层电离层探测星载HF_SAR系统分析与成像处理方法 646-651 1 第30卷, 第6期 * |
| 《北京航空航天大学学报》 20080229 宋曦 等 一种星载SAR模糊区回波信号仿真方法 144-147 1 第34卷, 第2期 * |
| 《宇航学报》 19921031 李春升 等 星载SAR数字成像处理及计算机仿真 89-95 1 , 第4期 * |
| 《宇航学报》 20060930 文竹 等 分布式小卫星SAR回波信号精确仿真方法研究 909-913 1 第27卷, 第5期 * |
| 《电子学报》 20050630 徐华平 等 分布式小卫星SAR回波信号的相关性 965-968 1 第33卷, 第6期 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102466799B (en) * | 2010-10-29 | 2013-06-26 | 中国科学院电子学研究所 | Method for simulating interference SAR (Synthetic Aperture Radar) echo data based on POS (Posture) motion data |
| CN102466799A (en) * | 2010-10-29 | 2012-05-23 | 中国科学院电子学研究所 | Method for simulating interference SAR (Synthetic Aperture Radar) echo data based on POS (Posture) motion data |
| CN102331576A (en) * | 2011-07-28 | 2012-01-25 | 北京航空航天大学 | Method for acquiring aiming point of SAR beam bunching work mode |
| CN102331576B (en) * | 2011-07-28 | 2013-01-30 | 北京航空航天大学 | Method for acquiring aiming point of SAR beam bunching work mode |
| CN103576148A (en) * | 2012-08-07 | 2014-02-12 | 中国科学院电子学研究所 | Method for simulating satellite-borne SAR range ambiguity noise image |
| CN103576148B (en) * | 2012-08-07 | 2015-12-16 | 中国科学院电子学研究所 | The method of simulation satellite-borne SAR range ambiguity noise image |
| CN102879768A (en) * | 2012-09-14 | 2013-01-16 | 北京航空航天大学 | Satellite-borne synthetic aperture radar (SAR) high-fidelity echo simulation method based on steady-state radar cross section (RCS) |
| CN102879768B (en) * | 2012-09-14 | 2015-01-21 | 北京航空航天大学 | Satellite-borne synthetic aperture radar (SAR) high-fidelity echo simulation method based on steady-state radar cross section (RCS) |
| CN103558592A (en) * | 2013-10-08 | 2014-02-05 | 北京航空航天大学 | Satellite-borne SAR echo data simulation method based on MPI parallel computing |
| CN103558592B (en) * | 2013-10-08 | 2015-12-02 | 北京航空航天大学 | A kind of satellite-borne SAR Echo searching method based on MPI parallel computation |
| CN109444881A (en) * | 2018-10-23 | 2019-03-08 | 中国电子科技集团公司第三十八研究所 | A kind of secondary surface layer detection radar substar pulse precise positioning method |
| CN109444881B (en) * | 2018-10-23 | 2020-06-26 | 中国电子科技集团公司第三十八研究所 | Subsurface detection radar sub-satellite pulse accurate positioning method |
| CN109782280A (en) * | 2019-03-06 | 2019-05-21 | 中国科学院电子学研究所 | Based on high rail SAR antenna distance in calibration satellite to directional diagram measuring method |
| CN110275140A (en) * | 2019-06-19 | 2019-09-24 | 西安电子科技大学 | Satellite-borne SAR beam sweeping method based on parabola antenna |
| CN110275140B (en) * | 2019-06-19 | 2021-03-05 | 西安电子科技大学 | Satellite-borne SAR beam scanning method based on parabolic antenna |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101846740B (en) | 2011-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101846740B (en) | Satellite-loaded SAR specified latitude area echo simulation method | |
| CN106338753B (en) | One kind being based on earth station/inter-satellite link/GNSS combined measurement geostationary orbit constellation orbit determination method | |
| CN107765226B (en) | SAR satellite radar echo simulation method, system and medium | |
| CN103197291B (en) | Satellite-borne synthetic aperture radar (SAR) echo signal simulation method based on non-stop walking model | |
| CN112070894B (en) | Real environment navigation multipath real-time simulation method, device, medium and electronic equipment | |
| CN107238824B (en) | Satellite-borne SAR image geometric accurate correction method based on priori dem data | |
| CN106405589A (en) | Method and device for determining global ionized layer grid model | |
| CN102288964A (en) | Imaging processing method for spaceborne high-resolution synthetic aperture radar | |
| CN101915920A (en) | High-resolution imaging method for earth synchronous orbit synthetic aperture radar satellite | |
| CN107727101B (en) | Three-dimensional attitude information rapid resolving method based on dual-polarized light vector | |
| CN107300700B (en) | Agile synthetic aperture radar satellite bunching mode attitude maneuver demand calculation method | |
| CN104048664A (en) | Autonomous orbit determination method of navigation satellite constellation | |
| CN103344958B (en) | Based on the satellite-borne SAR high-order Doppler parameter evaluation method of almanac data | |
| CN110456304A (en) | Airborne DF and location method | |
| CN102621994A (en) | Control method of geosynchronous earth orbit (GEO) synthetic aperture radar (SAR) for covering all over China | |
| CN105444778A (en) | Star sensor in-orbit attitude determination error obtaining method based on imaging geometric inversion | |
| Shim et al. | CEDAR‐GEM challenge for systematic assessment of ionosphere/thermosphere models in predicting TEC during the 2006 December storm event | |
| CN105182387A (en) | Beidou-three-carrier-based signal single epoch method for determining dynamic-dynamic ambiguity | |
| Huang et al. | Research on UAV flight performance test method based on dual antenna GPS/ins integrated system | |
| CN103728617A (en) | Bi-static synthetic aperture radar time-domain fast imaging method | |
| Kumar et al. | The global positioning system: Popular accuracy measures | |
| CN106019346B (en) | Single-star positioning method based on two-way communication co-located auxiliary | |
| CN103487808A (en) | Flight path simulation method of variable-parameter missile-borne bunching SAR in locking mode | |
| Vigneau et al. | Neural networks algorithms prototyping to mitigate GNSS multipath for LEO positioning applications | |
| CN112379398B (en) | Earth-moon space satellite navigation positioning method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110427 Termination date: 20150517 |
|
| EXPY | Termination of patent right or utility model |