CN112526518A - Distributed InSAR satellite global seamless mapping design method and system - Google Patents
Distributed InSAR satellite global seamless mapping design method and system Download PDFInfo
- Publication number
- CN112526518A CN112526518A CN202011467356.8A CN202011467356A CN112526518A CN 112526518 A CN112526518 A CN 112526518A CN 202011467356 A CN202011467356 A CN 202011467356A CN 112526518 A CN112526518 A CN 112526518A
- Authority
- CN
- China
- Prior art keywords
- satellite
- adjacent
- calculating
- design
- overlapping
- 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
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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Radar, Positioning & Navigation (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Electromagnetism (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Image Processing (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention provides a global seamless mapping design method for a distributed InSAR satellite. The method comprises the following implementation steps: (1) calculating the bandwidth of each wave position and the overlapping degree of the wave positions according to the wave position design result of the satellite system; (2) calculating the overlapping degree of adjacent visible bands according to the satellite orbit height; (3) calculating an overlapping error introduced by forecasting the relative positions of the two stars; (4) calculating an overlapping error introduced by system time synchronization; (5) calculating the relative motion displacement of the two satellites during imaging according to the configuration of the distributed satellite formation; (6) adjusting the SAR sampling start time position in real time through the InSAR system imaging start-stop time, and correcting the relative motion displacement of the two satellites; (7) and calculating DSM bandwidth and side direction overlapping degree of the InSAR system. The method can be used for designing a distributed InSAR double-star SAR system, and solves the problem that DSM bandwidth and adjacent DSM lateral overlapping of adjacent strips are deteriorated due to double-star relative displacement in a formation satellite imaging process.
Description
Technical Field
The invention relates to the technical field of aerospace systems, in particular to a global seamless mapping design method and system for a distributed InSAR satellite.
Background
Interferometric synthetic aperture radar (InSAR) is an important remote sensing means for obtaining high-precision ground elevation models (DSMs). The method comprises the steps of observing the same area at different viewing angles by using two SAR antennas distributed along a vertical course, carrying out interference processing on two acquired complex SAR images, solving the slope distance difference between the phase center of a main radar antenna and a secondary radar antenna and a target, and further obtaining a DSM (digital surface model) of an observation area. The distributed satellite InSAR system installs two SAR on two flying satellites in formation and simultaneously observes the earth, can overcome the problems of time decoherence and low baseline precision and the like of repeated navigation of the InSAR, and can obtain high-precision DSM.
When the distributed InSAR satellite operates in orbit, the ground area images with limited width can be obtained only in a strip mode during each voyage, and the ground area images obtained by multiple voyages are inevitably spliced for obtaining DSM information of all target areas. The side direction overlapping is also called transverse overlapping, in the field of space-based surveying and mapping, particularly refers to a part with the same ground image on adjacent image sheets shot along two adjacent air routes, and mainly aims to connect adjacent ground objects on the adjacent images of the adjacent air routes.
Therefore, under the condition of certain imaging bandwidth, the limited navigation times of the satellite and the adjacent route DSM side overlapping requirements are mutually restricted, if a smaller navigation times is pursued on one side, namely higher mapping efficiency is pursued, the side overlapping area is possibly insufficient, so that adjacent images cannot be connected, and a 'mapping drain area' can be even generated under extreme conditions; if the side overlapping of adjacent images is pursued conservatively, the mapping efficiency is reduced obviously, and the satellite use efficiency is affected.
The DSM bandwidth and the sidewise overlapping degree of the distributed InSAR satellite are important indexes of a satellite system, and the surveying and mapping efficiency of the satellite system is directly influenced, so how to realize the optimal design of the DSM bandwidth and the sidewise overlapping degree of the distributed InSAR satellite becomes one of important work for designing the distributed InSAR satellite system. With the rapid development of the satellite-borne InSAR technology, the requirement for the mapping efficiency of the distributed InSAR satellite is higher and higher, and the DSM bandwidth and the design margin of the lateral superposition are more and more tense, so that how to improve the lateral superposition degree of the DSM product so as to release the wave position design and the satellite orbit design margin becomes a direction which needs to be researched intensively.
Through retrieval, patent document CN108011746A relates to an IP-level global internet topology mapping method based on Traceroute and SNMP protocol. The number of anonymous nodes can be effectively reduced, so that the obtained preliminary topological graph is as concise and accurate as possible; and the number of anonymous nodes can be further reduced, the real information of some anonymous nodes can be identified, and meanwhile, the topological graph can be further expanded and strengthened, so that the topological graph is closer to the actual situation. The prior art mainly solves the technical problems that a global internet topology mapping method is adopted, and how to realize the optimization design of the distributed InSAR satellite DSM bandwidth and the sidewise overlapping degree is not solved.
Through retrieval, patent document CN103363959B discloses a stereo mapping imaging system and method based on separation load satellite formation, which combines sunlight ghost imaging technology, separation load satellite formation technology and compressive sensing theory, studies formation design from the perspective of positive and negative problems, establishes an accurate satellite orbit dynamics model, studies a correction method of formation under J2 perturbation, effectively inhibits the long-term drift of separation load formation along the track direction, and designs three pearl necklace formation configurations with pearl necklace formation as the background. However, the prior art mainly solves the technical problem of how to realize the optimal design of the DSM bandwidth and the sidewise overlapping degree of the distributed InSAR satellites based on the implementation approach of the stereo mapping imaging of the separated load satellite formation.
Through retrieval, a paper "global land surveying and mapping satellite formation configuration research" mainly demonstrates the requirement of the distributed SAR on the inter-satellite baseline in global land surveying and mapping work, and does not solve the technical problem of how to realize the optimization design of the distributed InSAR satellite DSM bandwidth and the sidewise overlapping degree.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a distributed InSAR satellite global seamless mapping design method and a distributed InSAR satellite global seamless mapping design system. In the existing distributed InSAR satellite design, in order to ensure sufficient lateral overlapping requirements, a method of increasing the overlapping degree of adjacent wave positions and increasing the overlapping degree between visible bands of two adjacent orbits is often adopted, and the method obviously reduces the satellite mapping efficiency. The invention provides a global seamless mapping design method for a distributed InSAR satellite, which can effectively solve the contradiction between lateral overlapping and mapping efficiency.
The invention provides a global seamless mapping design method for a distributed InSAR satellite, which comprises the following steps:
designing a track: calculating the overlapping degree of adjacent visible bands by designing the satellite orbit height;
wave position design step: calculating the bandwidth of each wave position and the overlapping degree of the wave positions through the design of the wave positions of the satellite system;
track forecasting: calculating an overlay error introduced by relative position prediction of a main satellite and an auxiliary satellite;
time synchronization step: overlapping errors caused by inconsistent time of the main satellite and the auxiliary satellite are calculated;
and (3) designing formation configuration: calculating relative motion displacement of the primary star and the secondary star during imaging through formation configuration;
and a result obtaining step: and calculating DSM bandwidth and side direction overlapping degree of the InSAR system.
Preferably, the SAR sampling start time position is adjusted in real time in the formation configuration step, and the relative displacement is corrected.
Preferably, the visible band in the track design step is the incidence angle range of all available wave bits of the SAR, and the overlap region of the available incidence angle ranges of two adjacent tracks SAR is calculated through the track design result.
Preferably, the sampling start time error, the sampling start stepping error and the slant range error introduced by the SAR hardware system are considered in the wave position design step.
Preferably, the maximum possible effect on the overlapping area of adjacent imaging bands is calculated by grouping satellite orbit prediction errors in the orbit prediction step.
Preferably, the maximum possible impact on the overlapping area of adjacent imaging bands is calculated by the formation of satellite time errors in the time synchronization step.
Preferably, in the formation configuration designing step, according to the satellite mission requirements, the satellites need to form the spatial position relation required for executing the mission through the current formation configuration during the in-orbit operation so as to obtain the required baseline and further complete the mapping mission.
Preferably, in the formation configuration designing step, the maximum influence which may be exerted on the overlapping area of the adjacent imaging bands is calculated by the formation satellite configuration design result.
Preferably, the position relation of the imaging start-stop time double stars is calculated according to the precise orbit forecasting result, the position of the SAR of the main star is kept unchanged according to the positions of the double stars at the imaging start-stop time, and the SAR of the auxiliary star is subjected to linear fitting according to the sampling start time at different times, so that the SAR of the auxiliary star is consistent with the ground position of the footprint of the SAR of the main star.
The invention provides a distributed InSAR satellite global seamless mapping design system, which comprises:
a track design module: calculating an overlapping area of usable incidence angle ranges of two adjacent orbits of the SAR to obtain the overlapping degree between adjacent visible bands of the SAR by designing the satellite orbit height;
wave position design module: calculating the overlapping area observed by adjacent wave positions according to the wave position design result to obtain the overlapping degree of the adjacent wave positions;
the track forecasting module: calculating the maximum influence possibly caused on the overlapping area of adjacent imaging bands formed by adjacent visible bands and adjacent wave bits through the orbit prediction error of the formation satellite;
a time synchronization module: calculating the maximum influence possibly caused on the overlapping area of adjacent imaging bands formed by adjacent visible bands and adjacent wave bits through the synchronous error of the relative time of the primary satellite and the secondary satellite;
a formation configuration module: during the in-orbit operation of the satellite, the spatial position relation required by the task is formed through the current formation configuration so as to obtain the required base line and further complete the mapping task.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the method, the double-satellite relative movement displacement is corrected in real time in orbit through the auxiliary satellite sampling initial time stepping parameter setting, the problem of side overlapping deterioration of adjacent strips DSMs due to double-satellite relative displacement in the formation satellite imaging process can be effectively solved, and engineering design allowance is released.
2. The invention can effectively solve the contradiction between the collateral superposition and the mapping efficiency through a global seamless mapping design method of the distributed InSAR satellite, and effectively solve the technical problems that the traditional distributed InSAR satellite system design does not adopt special measures aiming at the relative motion error of the two stars during imaging, and the enough DSM bandwidth is ensured only by increasing the imaging bandwidth of the single-star SAR through wave position design, thereby ensuring the enough DSM collateral superposition.
3. The method can be used for designing a distributed InSAR double-star SAR system, and solves the problem that DSM bandwidth and adjacent DSM lateral overlapping of adjacent strips are deteriorated due to double-star relative displacement in a formation satellite imaging process.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a processing step diagram of a distributed InSAR satellite global seamless mapping design method of the present invention;
FIG. 2 is a schematic diagram of a Master satellite imaging band region of a distributed InSAR satellite;
FIG. 3 is a schematic diagram of a satellite imaging band region of a distributed InSAR satellite;
FIG. 4 is a schematic diagram of the DSM available area in a distributed InSAR satellite;
FIG. 5 is a DSM usable area map after correcting the phase shift by the distributed InSAR satellite global seamless mapping design method of the present invention;
FIG. 6 is a schematic diagram of a footprint coincidence region of a primary satellite and a secondary satellite after correction phase shift by the distributed InSAR satellite global seamless mapping design method of the present invention;
FIG. 7 is a schematic diagram of an InSAR satellite DSM side overlay;
FIG. 8 is a schematic diagram of the side-by-side overlap of the InSAR satellite DSM after correction of the relative displacement by the distributed InSAR satellite global seamless mapping design method of the present invention;
FIG. 9 is a representation of the relative displacement of the two-star ground footprint in the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 to 8, the distributed InSAR satellite global seamless mapping design method provided by the present invention includes the following steps:
designing a track: calculating the overlapping degree of adjacent visible bands by designing the satellite orbit height; the track design mainly determines the overlapping degree between adjacent visible bands, the overlapping between the adjacent visible bands is mainly ensured by the track design and is one of main bearing indexes of system lateral overlapping design allowance, and the overlapping area of the usable incidence angle range of the SAR of two adjacent tracks is calculated through the track design result, namely the overlapping degree between the adjacent visible bands of the SAR.
Wave position design step: calculating the bandwidth of each wave position and the overlapping degree of the wave positions through the design of the wave positions of the satellite system; the wave position design mainly determines the single wave position imaging bandwidth of the SAR of the main satellite and the auxiliary satellite, is a main index for supporting the DSM bandwidth and is one of main bearing indexes of the system side overlapping design allowance, and the specific design method is that the overlapping area observed by adjacent wave positions is calculated through the wave position design result, namely the overlapping degree of the adjacent wave positions.
Track forecasting: calculating an overlay error introduced by relative position prediction of a main satellite and an auxiliary satellite; satellite mission performance is calculated primarily on time-extrapolated precision orbit data, and therefore, dual-satellite orbit predictions will also have an impact on DSM bandwidth. The specific design method is that the maximum influence possibly caused on the overlapping area of adjacent imaging bands is calculated through the orbit prediction error of the formation satellite.
Time synchronization step: overlapping errors caused by inconsistent time of the main satellite and the auxiliary satellite are calculated; the synchronization error of the two-satellite relative time directly affects the consistency of the two-satellite ground footprint, thereby affecting the available DSM bandwidth, and needs to be considered during design, and the two-satellite time synchronization precision is related to the system design level and the basic production level. The specific design method is to calculate the maximum influence possibly caused to the overlapping area of adjacent imaging bands through the time error of the formation satellite.
And (3) designing formation configuration: calculating relative motion displacement of the primary star and the secondary star during imaging through formation configuration; according to the requirement of a satellite task, the satellite needs to form a spatial position relation required by the task through the current formation configuration during the in-orbit operation so as to obtain a required base line and further complete the mapping task. The distributed InSAR satellite works in a one-shot double-receiving mode and is limited by a formation working principle, the two satellites simultaneously work, relative motion of the two satellites exists, and the displacement of ground SAR beam footprints introduced by the change of the slant distance introduced by the motion of the two satellites can influence the DSM bandwidth, so that the collateral overlapping index of a surveying and mapping product is influenced. The specific design method is to calculate the maximum influence possibly caused on the overlapping area of adjacent imaging bands through the formation satellite configuration design result.
And a result obtaining step: calculating DSM bandwidth and side direction overlapping degree of the InSAR system;
according to the inventionPreferred embodiment(s) of the inventionFurther, it is possible toAnd (4) explanation.
Based on the above embodiment, the present invention needs to adjust the position of the SAR sampling start time in real time and correct the relative displacement. Namely, when an SAR working instruction packet is compiled, the double-satellite relative motion displacement is corrected in real time in orbit by setting a parameter of sampling start time stepping so as to solve the problem of deterioration of DSM bandwidth and adjacent DSM lateral overlapping caused by the double-satellite relative displacement in the formation satellite imaging process. Calculating the position relation of imaging start-stop time double stars according to a precision orbit prediction result, keeping a main satellite SAR unchanged according to the imaging start-stop time double star position, linearly fitting an auxiliary satellite SAR according to sampling start time of different times to enable the auxiliary satellite SAR to be consistent with the ground position of a main satellite SAR footprint, determining the sampling start time stepping of the auxiliary satellite SAR, injecting a conventional SAR instruction packet on the main satellite, setting the sampling start time and the sampling start time stepping of the auxiliary satellite SAR instruction packet on the auxiliary satellite, calculating a stepping error by 25ns according to a 40MHz clock, and having less than 5m and negligible influence on the ground footprint position; during imaging, the auxiliary satellite performs sampling initial adjustment in an on-orbit real-time manner, the sampling initial adjustment is consistent with the ground position of the main satellite SAR footprint, and relative displacement correction is completed, so that DSM bandwidth and side-to-side overlapping are improved.
Based on the above embodiments, in the wave position design process, the invention considers the sampling start time error, the sampling start stepping error, the skew error and other factors introduced by the SAR hardware system, and the influence of the system on the DSM bandwidth needs to be considered in the overall design.
The specific embodiment is as follows:
the results of the design are shown in Table 1, with reference to the design parameters of the TanDEM-X system in Germany.
TABLE 1 satellite System parameter design results
1. Track design
In the orbit design, design factors such as satellite load, energy, thermal control and structure are comprehensively considered, relevant requirements such as carrying capacity are considered, the satellite orbit design is carried out, and the overlapping condition between adjacent visible bands is calculated.
According to the calculation of the parameter design result of the satellite system in the table 1, the overlapping between the adjacent visible bands is better than 12.5 km.
2. Wave position design:
according to the requirement of a satellite task, designing satellite parameters, comprehensively considering the height of a satellite orbit, the carrier frequency of a radar and working wave position parameters, completing SAR wave position design, and calculating the overlapping condition between adjacent wave positions. According to the calculation of the parameter design result of the satellite system shown in the table 1, the wave position overlapping degree is better than 8 km.
3. Track forecasting:
the forecasting precision is 10m by referring to design parameters of a German TanDEM-X system.
4. Time synchronization:
and referring to design parameters of a German TanDEM-X system, the time synchronization precision is converted into the ground distance of 5 m.
5. Designing formation configuration and correcting relative displacement:
the imaging time is set to be 5 minutes, 10 groups of configurations with the formation configuration size of 300m-1200m are designed, the statistical double star ground footprint relative displacement result is shown in figure 8, and the maximum value reaches 946 m.
6. Computing system DSM bandwidth and side lap:
according to the simulation parameter setting, the two stars work for 5 minutes, DSM bandwidth and side overlap design results are shown in table 2, and the simulation results show that the method can effectively solve the problem of side overlap deterioration of adjacent strips DSMs caused by relative displacement of the two stars in the formation satellite imaging process, and release engineering design allowance.
TABLE 2 comparison of design method results
| DSM bandwidth | DSM side lap | |
| Conventional design | 28.9km | 0.8km |
| Method for producing a composite material | 29.9km | 2.8km |
The traditional distributed InSAR satellite system design does not take special measures aiming at the relative motion error of the two satellites during imaging, only the enough DSM bandwidth is ensured by increasing the imaging bandwidth of the single-satellite SAR through wave position design, and then the enough DSM lateral overlapping is ensured.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A global seamless mapping design method for a distributed InSAR satellite is characterized by comprising the following steps:
designing a track: calculating the overlapping degree of adjacent visible bands by designing the satellite orbit height;
wave position design step: calculating the bandwidth of each wave position and the overlapping degree of the wave positions through the design of the wave positions of the satellite system;
track forecasting: calculating an overlay error introduced by relative position prediction of a main satellite and an auxiliary satellite;
time synchronization step: overlapping errors caused by inconsistent time of the main satellite and the auxiliary satellite are calculated;
and (3) designing formation configuration: calculating relative motion displacement of the primary star and the secondary star during imaging through formation configuration;
and a result obtaining step: and calculating DSM bandwidth and side direction overlapping degree of the InSAR system through overlapping degree of adjacent visual bands, the bandwidth of each wave position and the overlapping degree between the wave positions, overlapping errors introduced by forecasting of relative positions of a main satellite and an auxiliary satellite and overlapping errors introduced by inconsistent satellite and auxiliary satellite time.
2. The distributed InSAR satellite global seamless mapping design method of claim 1, wherein in the formation configuration step, SAR sampling start time position is adjusted in real time to correct relative displacement.
3. The distributed InSAR satellite global seamless mapping design method according to claim 1, characterized in that the visible band in the orbit design step is the incident angle range of all available wave positions of SAR, and the overlap region of the incident angle ranges available for two adjacent orbits of SAR is calculated through the orbit design result.
4. The distributed InSAR satellite global seamless mapping design method according to claim 1, characterized in that the sampling start time error, the sampling start step error and the slant range error introduced by SAR hardware system are considered in the wave position design step.
5. The distributed InSAR satellite global seamless mapping design method according to claim 1, wherein the maximum influence on the overlapping area of adjacent imaging bands is calculated by the formation satellite orbit prediction error in the orbit prediction step.
6. The distributed InSAR satellite global seamless mapping design method of claim 1, wherein the maximum possible impact on the overlapping area of adjacent imaging bands is calculated by the formation of satellite time errors in the time synchronization step.
7. The distributed InSAR satellite global seamless mapping design method of claim 1, wherein in the formation configuration design step, according to the satellite task requirement, the satellite needs to form the spatial position relation required by the task execution through the current formation configuration during the in-orbit operation period to obtain the required baseline to complete the mapping task.
8. The distributed InSAR satellite global seamless mapping design method according to claim 1, wherein in the formation configuration design step, the maximum influence possibly caused to the overlapping area of adjacent imaging bands is calculated through the formation satellite configuration design result.
9. The distributed InSAR satellite global seamless mapping design method according to claim 1, characterized in that the position relation of the imaging start-stop time double-star is calculated according to the precise orbit prediction result, the position of the primary star SAR is kept unchanged according to the imaging start-stop time double-star position, and the secondary star SAR is linearly fitted according to the sampling start time of different times, so that the primary star SAR and the ground of the footprint of the primary star SAR are consistent.
10. A distributed InSAR satellite global seamless mapping design system, comprising:
a track design module: calculating an overlapping area of usable incidence angle ranges of two adjacent orbits of the SAR to obtain the overlapping degree between adjacent visible bands of the SAR by designing the satellite orbit height;
wave position design module: calculating the overlapping area observed by adjacent wave positions according to the wave position design result to obtain the overlapping degree of the adjacent wave positions;
the track forecasting module: calculating the maximum influence possibly caused on the overlapping area of adjacent imaging bands formed by adjacent visible bands and adjacent wave bits through the orbit prediction error of the formation satellite;
a time synchronization module: calculating the maximum influence possibly caused on the overlapping area of adjacent imaging bands formed by adjacent visible bands and adjacent wave bits through the synchronous error of the relative time of the primary satellite and the secondary satellite;
a formation configuration module: during the in-orbit operation of the satellite, the spatial position relation required by the task is formed through the current formation configuration so as to obtain the required base line and further complete the mapping task.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011467356.8A CN112526518B (en) | 2020-12-14 | 2020-12-14 | Distributed InSAR satellite global seamless mapping design method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011467356.8A CN112526518B (en) | 2020-12-14 | 2020-12-14 | Distributed InSAR satellite global seamless mapping design method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112526518A true CN112526518A (en) | 2021-03-19 |
| CN112526518B CN112526518B (en) | 2022-10-25 |
Family
ID=74999580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011467356.8A Active CN112526518B (en) | 2020-12-14 | 2020-12-14 | Distributed InSAR satellite global seamless mapping design method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112526518B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115129075A (en) * | 2022-06-28 | 2022-09-30 | 上海交通大学 | Three-dimensional imaging satellite formation control starting and controlling method based on time-space combination mechanism |
| CN118092586A (en) * | 2024-04-25 | 2024-05-28 | 中国科学院空天信息创新研究院 | Hardware implementation method for time synchronization of satellite-borne distributed interference SAR timing signals |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101520511A (en) * | 2009-03-13 | 2009-09-02 | 北京航空航天大学 | Method for formation configuration of distributed satellites with synthetic aperture radars |
| CN104297751A (en) * | 2014-10-20 | 2015-01-21 | 西安电子科技大学 | Main and auxiliary SAR image fusion method of distributed satellite SAR system |
| US20150346336A1 (en) * | 2012-12-20 | 2015-12-03 | Thales Alenia Space Italia S.P.A. Con Unico Socio | Innovative Orbit Design For Earth Observation Space Missions |
| CN106556822A (en) * | 2016-11-09 | 2017-04-05 | 上海卫星工程研究所 | Spaceborne Sliding spotlight SAR pointing accuracy Orbital detection method |
| US20180172823A1 (en) * | 2015-06-16 | 2018-06-21 | Urthecast Corp | Systems and methods for remote sensing of the earth from space |
| CN109031297A (en) * | 2018-08-01 | 2018-12-18 | 北京空间飞行器总体设计部 | The distributed SAR configuration that primary is located at center, auxiliary star cartwheel forms into columns |
| CN109164448A (en) * | 2018-08-01 | 2019-01-08 | 北京空间飞行器总体设计部 | A kind of major-minor star distributed SAR detecting Integral imaging satellite system |
| CN109377075A (en) * | 2018-11-07 | 2019-02-22 | 长沙天仪空间科技研究院有限公司 | A kind of method for scheduling task based on prediction prediction |
| CN110907932A (en) * | 2019-11-26 | 2020-03-24 | 上海卫星工程研究所 | Distributed InSAR satellite height measurement precision influence factor analysis method and system |
| CN111693994A (en) * | 2020-04-30 | 2020-09-22 | 中国科学院空天信息创新研究院 | Airborne synthetic aperture radar route laying method, device, equipment and storage medium |
| CN111950877A (en) * | 2020-07-31 | 2020-11-17 | 上海卫星工程研究所 | Multi-satellite formation collaborative area imaging autonomous task planning method and system |
-
2020
- 2020-12-14 CN CN202011467356.8A patent/CN112526518B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101520511A (en) * | 2009-03-13 | 2009-09-02 | 北京航空航天大学 | Method for formation configuration of distributed satellites with synthetic aperture radars |
| US20150346336A1 (en) * | 2012-12-20 | 2015-12-03 | Thales Alenia Space Italia S.P.A. Con Unico Socio | Innovative Orbit Design For Earth Observation Space Missions |
| CN104297751A (en) * | 2014-10-20 | 2015-01-21 | 西安电子科技大学 | Main and auxiliary SAR image fusion method of distributed satellite SAR system |
| US20180172823A1 (en) * | 2015-06-16 | 2018-06-21 | Urthecast Corp | Systems and methods for remote sensing of the earth from space |
| CN106556822A (en) * | 2016-11-09 | 2017-04-05 | 上海卫星工程研究所 | Spaceborne Sliding spotlight SAR pointing accuracy Orbital detection method |
| CN109031297A (en) * | 2018-08-01 | 2018-12-18 | 北京空间飞行器总体设计部 | The distributed SAR configuration that primary is located at center, auxiliary star cartwheel forms into columns |
| CN109164448A (en) * | 2018-08-01 | 2019-01-08 | 北京空间飞行器总体设计部 | A kind of major-minor star distributed SAR detecting Integral imaging satellite system |
| CN109377075A (en) * | 2018-11-07 | 2019-02-22 | 长沙天仪空间科技研究院有限公司 | A kind of method for scheduling task based on prediction prediction |
| CN110907932A (en) * | 2019-11-26 | 2020-03-24 | 上海卫星工程研究所 | Distributed InSAR satellite height measurement precision influence factor analysis method and system |
| CN111693994A (en) * | 2020-04-30 | 2020-09-22 | 中国科学院空天信息创新研究院 | Airborne synthetic aperture radar route laying method, device, equipment and storage medium |
| CN111950877A (en) * | 2020-07-31 | 2020-11-17 | 上海卫星工程研究所 | Multi-satellite formation collaborative area imaging autonomous task planning method and system |
Non-Patent Citations (3)
| Title |
|---|
| 康冰锋等: "基于不同旁向重叠度的A3影像空三精度研究", 《测绘通报》 * |
| 李航舰等: "分布式星载SAR系统时间同步和波束同步误差分析", 《雷达学报》 * |
| 王东亮等: "基于立体模型重叠度的航空摄影航线设计", 《测绘学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115129075A (en) * | 2022-06-28 | 2022-09-30 | 上海交通大学 | Three-dimensional imaging satellite formation control starting and controlling method based on time-space combination mechanism |
| CN118092586A (en) * | 2024-04-25 | 2024-05-28 | 中国科学院空天信息创新研究院 | Hardware implementation method for time synchronization of satellite-borne distributed interference SAR timing signals |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112526518B (en) | 2022-10-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103983254B (en) | The motor-driven middle formation method of a kind of novel quick satellite | |
| CN112526518B (en) | Distributed InSAR satellite global seamless mapping design method and system | |
| CN101915920B (en) | High-resolution imaging method for earth synchronous orbit synthetic aperture radar satellite | |
| CN103217987B (en) | Agile satellite dynamic imaging posture adjustment method | |
| CN102968631B (en) | The automatic geometric of mountain area multispectral remote sensing satellite image is corrected and ortho-rectification method | |
| CN102636159B (en) | In-orbit geometrical self-calibration method for multi-mirror aerospace linear array camera system | |
| CN102230964B (en) | Geo-synchronous orbit synthetic aperture radar (GEO SAR) frequency modulation changeable standard imaging method under curve track model | |
| CN103033188B (en) | The autonomous method for synchronizing time of Navsat based on synthetic aperture observation | |
| CN110515078B (en) | Wave position design method for airspace coverage | |
| CN106249237A (en) | Big Squint SAR frequency domain imaging method under a kind of curvilinear path | |
| CN103345737A (en) | UAV high resolution image geometric correction method based on error compensation | |
| CN103487809A (en) | Onboard InSAR data processing method based on BP algorithm and time-varying baseline | |
| CN104133215B (en) | Synchronous orbit radar imaging method based on range migration fine adjustment and sub-band division | |
| CN105823469A (en) | GNSS high precision assisted unmanned plane aerotriangulation method | |
| CN103678787A (en) | Sub-satellite point circular geosynchronous orbit design method | |
| CN102735216A (en) | Adjustment processing method for CCD stereo camera three-line-array image data | |
| Tang et al. | The China ZY3-03 mission: Surveying and mapping technology for high-resolution remote sensing satellites | |
| CN102322863B (en) | Remote sensing satellite multi-satellite combined converse orbit and attitude determination method | |
| CN103336290A (en) | A method and a system for measuring baselines between adjacent formation satellites | |
| CN113514829A (en) | InSAR-oriented initial DSM block adjustment method | |
| CN103134492A (en) | Agile imaging satellite linear scan strip pre-generating method based on point target and satellite three-axis gesture rapid determining method | |
| CN103197316A (en) | Protective phase airborne interference synthetic aperture radar (SAR) terrain altitude self-adaption motion compensation method | |
| CN115373423A (en) | Formation capture method for commercial satellite | |
| Fan et al. | A new Greenland digital elevation model derived from ICESat-2 during 2018–2019 | |
| CN103793609A (en) | Strict imaging model and positioning method considering satellite fluttering |
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 |