CN116054925A - Remote sensing satellite service data structure construction method based on Beidou satellite constellation - Google Patents
Remote sensing satellite service data structure construction method based on Beidou satellite constellation Download PDFInfo
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- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18513—Transmission in a satellite or space-based system
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- H—ELECTRICITY
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Abstract
The application discloses a remote sensing satellite service data structure construction method based on Beidou satellite constellation, which adopts globalization service mode design under sparse measurement and control conditions, and service satellite communication module design and instruction and key information comprehensive coding of fusion BDS star chain transmission. Has the following advantages: the global service mode of remote sensing service satellite global measurement and control and service is realized by utilizing BDS global service advantages; and designing a service satellite chain transmission module, realizing inter-satellite interaction with the BDS, and realizing service instruction uploading and key comprehensive information downloading by utilizing the interaction capability between the BDS and the service satellites, between the BDS and the ground and between the service satellites and between the BDS and the ground, so as to realize globalization and minute-level service of on-orbit processing.
Description
Technical Field
The invention relates to the field of global measurement and control of on-orbit satellites and real-time release of global information, in particular to an on-orbit remote sensing satellite global real-time application service which can not form global measurement and control aiming at the layout regional distribution of ground measurement and control stations.
Background
Along with the continuous enhancement of the high-efficiency response to the earth observation requirement, the on-orbit processing becomes a necessary trend of earth remote sensing observation; high-aging earth observation is influenced by two aspects of on-orbit processing speed and data distribution aging, wherein the data distribution is the final key link for guaranteeing high-aging service.
At present, the domestic commercial remote sensing satellite ground measurement and control is based on domestic ground measurement and control stations and few overseas measurement and control stations, the service satellite service adopts a mode of injecting instructions one day in advance to carry out satellite measurement and control, and faces the global natural disaster monitoring demands of frequent fires, earthquakes and the like, a larger measurement and control blind area exists for the overseas observation demands, the first time response of the on-orbit commercial satellite and the first time global release of on-orbit real-time processing data products cannot be ensured, and the service quality of on-orbit processing is greatly reduced.
The response timeliness of the remote sensing satellite on-orbit processing is not only limited by the on-orbit computing capacity under the condition of limited on-satellite resources, but also influenced by the command and data release capacity; aiming at the characteristics of original design and insufficient ground measurement and control of a domestic commercial earth observation remote sensing satellite, the invention provides a global relay measurement and control service system integrating a Beidou satellite navigation system (BDS), realizes the full-time space element interaction of a service star and the BDS, achieves the real-time uploading and downloading of service instructions and data products, and improves the global service capability under the satellite constellation region measurement and control condition.
Disclosure of Invention
Aiming at the characteristics of regional distribution of ground measurement and control layout of a commercial remote sensing satellite constellation and the construction requirements of on-orbit intelligent processing globalization service, the invention provides a globalization service mode for realizing global measurement and control and service of a remote sensing service satellite by utilizing BDS globalization service advantages; and designing a service satellite chain transmission module, realizing inter-satellite interaction with the BDS, and realizing service instruction uploading and key comprehensive information downloading by utilizing the interaction capability between the BDS and the service satellites, between the BDS and the ground and between the service satellites and between the BDS and the ground, so as to realize globalization and minute-level service of on-orbit processing.
In order to solve the technical problems, the invention adopts the following technical scheme:
the method adopts globalization service mode design under sparse measurement and control conditions, and integrates BDS star chain transmission service satellite communication module design and instruction and key information comprehensive coding.
Further, the method comprises the steps of:
step 1: constellation task planning, which realizes the generation of the observation instruction of the task target, and comprises three steps of satellite resource matching, observation time window calculation and satellite service instruction generation;
step 2: the design of the uploading instruction is that the maximum support of 560 bits is provided for single communication service of the Beidou third-generation global short message, the uploading instruction is required to be designed, and the design requirement of transmission is ensured;
step 3: the key information design is to carry out high-reduction extraction and expression on the on-orbit processing result, so as to meet the design requirement of globalization service;
step 4: the globalization service mode adopts a ground station and Beidou communication dual-mode service mode, wherein in order to meet the Beidou communication requirement, a remote sensing satellite is provided with an inter-satellite communication module and a Beidou terminal module to realize information stream transmission;
step 5: the remote sensing satellite performs uplink and downlink through the ground station in the measurement and control range of the ground station, so that the transmission requirements of uplink instructions, complete data and key information can be ensured; meanwhile, key information can be sent by a terminal through Beidou short messages, so that quick information release is realized;
step 6: and (3) out of the ground station measurement and control range, carrying out uplink and downlink transmission on satellite imaging instructions and key information based on the third-generation Beidou short message communication service.
Further, the step 1 includes a step 1.1 of satellite resource matching:
according to task target requirements, task satellite resource screening and matching are carried out, and a hierarchical screening and matching method is adopted to carry out task execution resource matching;
step 1.1.1, satellite screening is carried out based on the type requirement of a task target sensor;
and step 1.1.2, satellite screening is performed based on the task target resolution requirements.
Further, the step 1 further includes a step 1.2 of calculating an observation time window of the task target:
the satellite orbit data and cloud amount information are led in, and the visible relation between the satellite and the task target is utilized to obtain an observation time window set of the task target, wherein each observation time window is as follows:
wherein, sat is the name of the satellite,
for observing the start time, +.>
For the end time of observation>
For observing the yaw angle +.>
For the observation time sun altitude, +.>
The cloud quantity is the observation time;
and removing the observation time window which does not meet the constraint conditions from the observation time window set, wherein the constraint conditions are as follows:
side swing constraint: the satellite has certain side-swinging capability, namely the maximum side-swinging angle of the satellite
At the same time, the task target demand sometimes specifies the maximum yaw angle requirement +.>
The observation roll angle needs to be smaller than the satellite roll capability and the task target roll angle, namely:
solar altitude constraint: for an optical satellite, the solar altitude angle needs to reach a certain angle, such as 20 degrees, so that optical observation can be effectively performed, and the solar altitude angle at the observation moment needs to be larger than the minimum solar altitude angle required by imaging
I.e.
Cloud cover constraint: for optical satellites, target observation cannot be performed through cloud and fog, and cloud amount constraint can be specified to improve the effective observation efficiency, and the cloud amount at the observation time is smaller than the maximum cloud amount required by imaging specification
I.e.
Further, the step 1 further includes a step 1.3 of generating an instruction:
and arranging the observation time window sets in ascending order according to the observation starting time, selecting the earliest time window of the observation starting time as an execution window, completing the execution of satellite matching and generating an imaging instruction.
Further, the uploading instruction in the step 2 is as follows:
the upper instruction=version number, satellite identification code, instruction type, imaging start time, task duration, imaging position longitude, imaging position latitude, side swing angle, gain setting, integral series setting and CRC check;
version number: the method comprises the steps of designing 1 byte of instruction version management information including instruction version marks, internal command tags, clear and secret states and the like;
satellite identification code: the system is designed to be 2 bytes for distinguishing different execution satellites;
instruction type: instruction application type is described, and 1 byte is designed;
imaging time is started: imaging task start time, designed to be 4 bytes;
task duration: imaging duration, integer seconds, designed to be 2 bytes;
imaging position longitude: imaging points to the longitude of the target point, is designed to be 4 bytes, and retains four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
imaging position latitude: imaging is directed to the latitude of the position of the target point, and is designed to be 4 bytes; the highest bit of the first byte is 1 to represent north latitude and 0 to represent south latitude;
side swing angle: the imaging yaw angle setting, designed to be 4 bytes; the highest bit of the first byte is 1 to represent left side swing, and 0 to represent right side swing;
gain setting: setting imaging gain, and designing the imaging gain to be 2 bytes;
setting an integral stage number: setting an integral series parameter of satellite imaging, wherein the integral series parameter consists of 4 integral series and is designed to be 4*4 =16 bytes;
CRC check: check code, designed as 2 bytes.
Further, the key information in the step 3 is designed as follows:
key information=target position longitude+target position latitude+imaging time+pixel area+target attribute information;
target position longitude: on-orbit processing identifies a target longitude, is designed to be 4 bytes, and reserves four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
target position latitude: the on-orbit processing identifies the target latitude, is designed to be 4 bytes, and reserves four valid digits after decimal point; the highest bit of the first byte is 1 to represent north latitude and 0 to represent south latitude;
imaging time: the imaging time adopts UTC time, which is expressed by XX minutes and XX seconds when XX is in XX year, XX month, XX day, XX, and each independent number X is expressed by 4 bits and is designed to be 7 bytes;
pixel area: the pixel area is represented by the square of the sensor spatial resolution, and is designed to be 1 byte;
target attribute information: the attribute information mainly comprises the category, area and attribute information of the on-orbit processing identification target; the target class defines a digital lookup table according to the on-orbit intelligent processing model, the type design is 1 byte, and the type in 255 is supported; the target area adopts pixel statistical area, is designed to be 3 bytes, and meets the requirement of tens of millions of data output; the target attribute information can be adjusted according to actual requirements, and 45 bytes of redundant design is reserved.
Further, the step 6 includes a step 6.1 of uplink instruction communication, and the uplink instruction communication flow is as follows:
step 6.1.1, performing task planning according to task requirements according to the step 1 and the step 2, generating satellite measurement and control instructions, and transmitting the instructions to a Beidou satellite by using a Beidou director;
step 6.1.2, the Beidou satellite utilizes constellation link communication to complete target satellite tracking according to the code number of the service satellite, and instruction relay transmission is carried out;
and 6.1.3, receiving a relay instruction by the Beidou terminal integrated with the service remote sensing satellite control, and finishing instruction decoding by using an instruction analysis module to guide the service satellite task to be executed.
Further, the step 6 further includes a step 6.2 of communicating key information, where the key information communication flow is as follows:
step 6.2.1, finishing data shooting and on-orbit real-time processing by the service satellite, finishing key information extraction, and finishing information expression according to the step 3;
step 6.2.2, the Beidou terminal integrated with the business remote sensing satellite control sends key information short message information to a Beidou satellite;
step 6.2.3, global information release is performed based on the Beidou constellation.
Compared with the prior art, the invention has the following technical effects:
the global service mode for realizing global measurement and control and service of the remote sensing service satellite by utilizing BDS global service advantages is provided; and designing a service satellite chain transmission module, realizing inter-satellite interaction with the BDS, and realizing service instruction uploading and key comprehensive information downloading by utilizing the interaction capability between the BDS and the service satellites, between the BDS and the ground and between the service satellites and between the BDS and the ground, so as to realize globalization and minute-level service of on-orbit processing.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. Like elements or portions are generally identified by like reference numerals throughout the several figures. In the drawings, elements or portions thereof are not necessarily drawn to scale.
FIG. 1 is a global service schematic based on BDS;
FIG. 2 is a flowchart of a sparse measurement and control globalization service.
Detailed Description
In embodiment 1, as shown in fig. 1, a method for constructing a remote sensing satellite service data structure based on a Beidou satellite constellation is implemented by adopting globalization service mode design under a sparse measurement and control condition, and integrating service satellite communication module design, instruction and key information comprehensive coding of BDS star chain transmission, and the detailed description will be given below with reference to fig. 1 and 2.
The global service mode design under the sparse measurement and control condition starts from the reality of the regional distribution of the ground measurement and control station, considers the global all-weather and all-day networking service characteristics and short message communication capability of the BDS, combines the 500km orbit layout characteristics of the service satellite, takes the BDS as a space relay, utilizes the global coverage service capability of the BDS, compensates the measurement and control blind area caused by the deficiency of the ground measurement and control station, and realizes the uploading and the downloading of the service satellite on the global arbitrary orbit surface instruction and information.
The method comprises the following steps:
step 1: constellation task planning, which realizes the generation of the observation instruction of the task target, and comprises three steps of satellite resource matching, observation time window calculation and satellite service instruction generation;
step 1.1, satellite resource matching
According to task target requirements (sensor type, resolution and the like), task satellite resource screening and matching are carried out, and a hierarchical screening and matching method is adopted to carry out task execution resource matching;
step 1.1.1, satellite screening is carried out based on the type requirement of a task target sensor;
and step 1.1.2, satellite screening is performed based on the task target resolution requirements.
Step 1.2, calculating an observation time window of the task target
The satellite orbit data and cloud amount information are led in, and the visible relation between the satellite and the task target is utilized to obtain an observation time window set of the task target, wherein each observation time window is as follows:
wherein, sat is the name of the satellite,
for observing the start time, +.>
For the end time of observation>
For observing the yaw angle +.>
For the observation time sun altitude, +.>
The cloud quantity is the observation time.
And removing the observation time window which does not meet the constraint conditions from the observation time window set, wherein the constraint conditions are as follows:
side swing constraint: in general, satellites have a certain yaw capacity, i.e. the maximum yaw angle of the satellite
At the same time, the task target demand sometimes specifies the maximum yaw angle requirement +.>
. The observation roll angle needs to be smaller than the satellite roll capability and the task target roll angle requirement, namely:
solar altitude constraint: for optical satellites, it is generally required that the solar altitude reaches a certain angle, such as 20 °, to effectively perform optical observation, and the solar altitude at the time of observation needs to be greater than the minimum solar altitude required by imaging
I.e.
Cloud cover constraint: for optical satellites, target observation cannot be performed through cloud and fog, etc., cloud constraints are generally specified to improve the effective observation efficiency. The cloud quantity at the observation time is smaller than the maximum cloud quantity required by imaging specification
I.e.
Step 1.3, instruction Generation
And arranging the observation time window sets in ascending order according to the observation starting time, selecting the earliest time window of the observation starting time as an execution window, completing the execution of satellite matching and generating an imaging instruction.
Step 2: the design of the uploading instruction is that the maximum support of 560 bits is provided for single communication service of the Beidou third-generation global short message, the uploading instruction is required to be designed, and the design requirement of transmission is ensured;
the upper instruction=version number+satellite identification code+instruction type+imaging start time+task duration+imaging position longitude+imaging position latitude+side swing angle+gain setting+integration series setting+crc check.
(1) Version number: the method comprises the steps of designing 1 byte of instruction version management information including instruction version marks, internal command tags, clear and secret states and the like;
(2) Satellite identification code: the system is designed to be 2 bytes for distinguishing different execution satellites;
(3) Instruction type: instruction application types, such as business instructions, are described, and are designed to be 1 byte;
(4) Imaging time is started: imaging task start time, designed to be 4 bytes;
(5) Task duration: imaging duration, typically an integer number of seconds, is designed to be 2 bytes;
(6) Imaging position longitude: imaging points to the longitude of the target point, is designed to be 4 bytes, and retains four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
(7) Imaging position latitude: imaging is directed to the latitude of the position of the target point, and is designed to be 4 bytes; the highest bit of the first byte is 1 to represent north latitude and 0 to represent south latitude;
(8) Side swing angle: the imaging yaw angle setting, designed to be 4 bytes; the highest bit of the first byte is 1 to represent left side swing, and 0 to represent right side swing;
(9) Gain setting: setting imaging gain, and designing the imaging gain to be 2 bytes;
(10) Setting an integral stage number: setting an integral series parameter of satellite imaging, wherein the integral series parameter is generally composed of 4 integral series and is designed to 4*4 =16 bytes;
(11) CRC check: a check code, designed as 2 bytes;
the total of 42 bytes completely meets the global service design requirement of the Beidou short message.
The results of the on-orbit service satellite simulation are shown in table 1;
table 1 Emulation Table of the data structure of the Instructions
The real-time release of the satellite shooting task in the global scope is an important precondition for guaranteeing the real-time performance of on-orbit processing; the service instruction generated by the construction method of the uploading instruction data structure can not only meet the accurate execution of the on-orbit task of the service satellite, but also meet the short message communication capability of BDS globalization service, provide possibility for real-time release of the globalization task of the satellite constellation in the sparse distribution state of the ground station, and realize the globalization service capability of the on-orbit real-time service of the satellite constellation.
Step 3: the key information design is to carry out high-reduction extraction and expression on the on-orbit processing result, meets the design requirement of globalization service, and has the following information design:
key information=target position longitude+target position latitude+imaging time+pixel area+target attribute information;
(1) Target position longitude: on-orbit processing identifies a target longitude, is designed to be 4 bytes, and reserves four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
(2) Target position latitude: the on-orbit processing identifies the target latitude, is designed to be 4 bytes, and reserves four valid digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
(3) Imaging time: the imaging time adopts UTC time, which is expressed by XX minutes and XX seconds when XX is in XX year, XX month, XX day, XX, and each independent number X is expressed by 4 bits and is designed to be 7 bytes;
(4) Pixel area: the pixel area is represented by the square of the sensor spatial resolution, and is designed to be 1 byte;
(5) Target attribute information: the attribute information mainly comprises the category, area and the like of the identification target of the on-orbit processing; the target class defines a digital lookup table according to the on-orbit intelligent processing model, the type design is 1 byte, and the type in 255 is supported; the target area adopts pixel statistical area, is designed to be 3 bytes, and meets the requirement of tens of millions of data output; the target attribute information can be adjusted according to actual requirements, and 45 bytes of redundant design is reserved;
the total of 20 bytes completely meets the global service design requirement of the Beidou short message.
Taking ship identification as an example, simulation results are shown in table 2;
table 2 simulation table of key information data structure
The data structure constructed by the invention is used for carrying out key information synthesis, not only can clearly express the key information extracted by on-orbit processing, but also can meet the byte length requirement of BDS globalization short message release, and the last barrier of on-orbit processing data stream global real-time release is opened.
Step 4: the globalization service mode adopts a ground station and Beidou communication dual-mode service mode; in order to meet the Beidou communication demand, the remote sensing satellite is carried with an inter-satellite communication module and a Beidou terminal module to realize information stream transmission;
step 5: the remote sensing satellite performs uplink and downlink through the ground station in the measurement and control range of the ground station, so that the transmission requirements of uplink instructions, complete data and key information can be ensured; meanwhile, key information can be sent by a terminal through Beidou short messages, so that quick information release is realized;
step 6: and (3) out of the ground station measurement and control range, carrying out uplink and downlink transmission on satellite imaging instructions and key information based on the third-generation Beidou short message communication service.
Step 6.1, the uplink instruction communication flow is as follows:
step 6.1.1, performing task planning according to task requirements according to the step 1 and the step 2, generating satellite measurement and control instructions, and transmitting the instructions to a Beidou satellite by using a Beidou director;
step 6.1.2, the Beidou satellite utilizes constellation link communication to complete target satellite tracking according to the code number of the service satellite, and instruction relay transmission is carried out;
step 6.1.3, the Beidou terminal integrated with the business remote sensing satellite control receives the relay instruction, and finishes instruction decoding by utilizing the instruction analysis module to guide the business satellite task to be executed;
step 6.2, the key information communication flow is as follows:
step 6.2.1, finishing data shooting and on-orbit real-time processing by the service satellite, finishing key information extraction, and finishing information expression according to the step 3;
step 6.2.2, the Beidou terminal integrated with the business remote sensing satellite control sends key information short message information to a Beidou satellite;
step 6.2.3, global information release is performed based on the Beidou constellation.
The description of the present invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (9)
1. The remote sensing satellite service data structure construction method based on the Beidou satellite constellation is characterized by comprising the following steps of: the method adopts globalization service mode design under the sparse measurement and control condition, and integrates the service satellite communication module design and instruction of BDS star chain transmission and key information comprehensive coding.
2. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 1, wherein the method comprises the following steps of: the method comprises the following steps:
step 1: constellation task planning, which realizes the generation of the observation instruction of the task target, and comprises three steps of satellite resource matching, observation time window calculation and satellite service instruction generation;
step 2: the design of the uploading instruction is that the maximum support of 560 bits is provided for single communication service of the Beidou third-generation global short message, the uploading instruction is required to be designed, and the design requirement of transmission is ensured;
step 3: the key information design is to carry out high-reduction extraction and expression on the on-orbit processing result, so as to meet the design requirement of globalization service;
step 4: the globalization service mode adopts a ground station and Beidou communication dual-mode service mode, wherein in order to meet the Beidou communication requirement, a remote sensing satellite is provided with an inter-satellite communication module and a Beidou terminal module to realize information stream transmission;
step 5: the remote sensing satellite performs uplink and downlink through the ground station in the measurement and control range of the ground station, so that the transmission requirements of uplink instructions, complete data and key information can be ensured; meanwhile, key information can be sent by a terminal through Beidou short messages, so that quick information release is realized;
step 6: and (3) out of the ground station measurement and control range, carrying out uplink and downlink transmission on satellite imaging instructions and key information based on the third-generation Beidou short message communication service.
3. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: the step 1 comprises the step 1.1 of satellite resource matching:
according to task target requirements, task satellite resource screening and matching are carried out, and a hierarchical screening and matching method is adopted to carry out task execution resource matching;
step 1.1.1, satellite screening is carried out based on the type requirement of a task target sensor;
and step 1.1.2, satellite screening is performed based on the task target resolution requirements.
4. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: step 1 further includes step 1.2 of calculating an observation time window of the task target:
the satellite orbit data and cloud amount information are led in, and the visible relation between the satellite and the task target is utilized to obtain an observation time window set of the task target, wherein each observation time window is as follows:
wherein, sat is the name of the satellite,
for observing the start time, +.>
For the end time of observation>
For observing the yaw angle +.>
For the observation time sun altitude, +.>
The cloud quantity is the observation time;
and removing the observation time window which does not meet the constraint conditions from the observation time window set, wherein the constraint conditions are as follows:
side swing constraint: the satellite has certain side-swinging capability, namely the maximum side-swinging angle of the satellite
At the same time, the task target demand sometimes specifies the maximum yaw angle requirement +.>
The observation roll angle needs to be smaller than the satellite roll capability and the task target roll angle, namely:
solar altitude constraint: solar altitude is required for optical satellitesThe optical observation can be effectively carried out only when a certain angle of 20 degrees is reached, and the solar altitude at the observation moment is required to be larger than the minimum solar altitude required by imaging
I.e.
Cloud cover constraint: for optical satellites, target observation cannot be performed through cloud and fog, and cloud amount constraint can be specified to improve the effective observation efficiency, and the cloud amount at the observation time is smaller than the maximum cloud amount required by imaging specification
I.e.
5. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: the step 1 further includes a step 1.3 of generating instructions:
and arranging the observation time window sets in ascending order according to the observation starting time, selecting the earliest time window of the observation starting time as an execution window, completing the execution of satellite matching and generating an imaging instruction.
6. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: the uploading instruction in the step 2 is as follows:
the upper instruction=version number, satellite identification code, instruction type, imaging start time, task duration, imaging position longitude, imaging position latitude, side swing angle, gain setting, integral series setting and CRC check;
version number: the method comprises the steps of designing 1 byte of instruction version management information including instruction version marks, internal command tags, clear and secret states and the like;
satellite identification code: the system is designed to be 2 bytes for distinguishing different execution satellites;
instruction type: instruction application type is described, and 1 byte is designed;
imaging time is started: imaging task start time, designed to be 4 bytes;
task duration: imaging duration, integer seconds, designed to be 2 bytes;
imaging position longitude: imaging points to the longitude of the target point, is designed to be 4 bytes, and retains four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
imaging position latitude: imaging is directed to the latitude of the position of the target point, and is designed to be 4 bytes; the highest bit of the first byte is 1 to represent north latitude and 0 to represent south latitude;
side swing angle: the imaging yaw angle setting, designed to be 4 bytes; the highest bit of the first byte is 1 to represent left side swing, and 0 to represent right side swing;
gain setting: setting imaging gain, and designing the imaging gain to be 2 bytes;
setting an integral stage number: setting an integral series parameter of satellite imaging, wherein the integral series parameter consists of 4 integral series and is designed to be 4*4 =16 bytes;
CRC check: check code, designed as 2 bytes.
7. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: the key information design in the step 3 is as follows:
key information=target position longitude+target position latitude+imaging time+pixel area+target attribute information;
target position longitude: on-orbit processing identifies a target longitude, is designed to be 4 bytes, and reserves four significant digits after decimal point; the highest bit of the first byte is 1 to represent east meridian, and 0 to represent west meridian;
target position latitude: the on-orbit processing identifies the target latitude, is designed to be 4 bytes, and reserves four valid digits after decimal point; the highest bit of the first byte is 1 to represent north latitude and 0 to represent south latitude;
imaging time: the imaging time adopts UTC time, which is expressed by XX minutes and XX seconds when XX is in XX year, XX month, XX day, XX, and each independent number X is expressed by 4 bits and is designed to be 7 bytes;
pixel area: the pixel area is represented by the square of the sensor spatial resolution, and is designed to be 1 byte;
target attribute information: the attribute information mainly comprises the category, area and attribute information of the on-orbit processing identification target; the target class defines a digital lookup table according to the on-orbit intelligent processing model, the type design is 1 byte, and the type in 255 is supported; the target area adopts pixel statistical area, is designed to be 3 bytes, and meets the requirement of tens of millions of data output; the target attribute information can be adjusted according to actual requirements, and 45 bytes of redundant design is reserved.
8. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: step 6 includes step 6.1, uplink instruction communication, the uplink instruction communication flow is as follows:
step 6.1.1, performing task planning according to task requirements according to the step 1 and the step 2, generating satellite measurement and control instructions, and transmitting the instructions to a Beidou satellite by using a Beidou director;
step 6.1.2, the Beidou satellite utilizes constellation link communication to complete target satellite tracking according to the code number of the service satellite, and instruction relay transmission is carried out;
and 6.1.3, receiving a relay instruction by the Beidou terminal integrated with the service remote sensing satellite control, and finishing instruction decoding by using an instruction analysis module to guide the service satellite task to be executed.
9. The method for constructing the remote sensing satellite service data structure based on the Beidou satellite constellation as claimed in claim 2, wherein the method comprises the following steps of: step 6 also includes step 6.2, key information communication, the key information communication flow is as follows:
step 6.2.1, finishing data shooting and on-orbit real-time processing by the service satellite, finishing key information extraction, and finishing information expression according to the step 3;
step 6.2.2, the Beidou terminal integrated with the business remote sensing satellite control sends key information short message information to a Beidou satellite;
step 6.2.3, global information release is performed based on the Beidou constellation.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116760456A (en) * | 2023-08-14 | 2023-09-15 | 上海航天空间技术有限公司 | Satellite data real-time transmission method and system for remote sensing monitoring of small-area mountain fire |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107370535A (en) * | 2017-06-26 | 2017-11-21 | 航天东方红卫星有限公司 | Incorporate based on microsatellite system timely responds to information acquisition method |
| CN108256822A (en) * | 2017-12-25 | 2018-07-06 | 航天恒星科技有限公司 | One kind is suitable for weather information secondary satellite imaging task planning system and method |
| CN111929719A (en) * | 2020-07-16 | 2020-11-13 | 中国科学院微小卫星创新研究院 | Low-orbit scientific satellite global strapdown system and method |
| CN114066201A (en) * | 2021-11-10 | 2022-02-18 | 北京微纳星空科技有限公司 | Real-time feedback remote sensing satellite task planning method and system |
| CN115345496A (en) * | 2022-08-19 | 2022-11-15 | 陕西航天技术应用研究院有限公司 | Imaging task planning method for remote sensing video satellite |
-
2023
- 2023-03-31 CN CN202310330582.9A patent/CN116054925A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107370535A (en) * | 2017-06-26 | 2017-11-21 | 航天东方红卫星有限公司 | Incorporate based on microsatellite system timely responds to information acquisition method |
| CN108256822A (en) * | 2017-12-25 | 2018-07-06 | 航天恒星科技有限公司 | One kind is suitable for weather information secondary satellite imaging task planning system and method |
| CN111929719A (en) * | 2020-07-16 | 2020-11-13 | 中国科学院微小卫星创新研究院 | Low-orbit scientific satellite global strapdown system and method |
| CN114066201A (en) * | 2021-11-10 | 2022-02-18 | 北京微纳星空科技有限公司 | Real-time feedback remote sensing satellite task planning method and system |
| CN115345496A (en) * | 2022-08-19 | 2022-11-15 | 陕西航天技术应用研究院有限公司 | Imaging task planning method for remote sensing video satellite |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116760456A (en) * | 2023-08-14 | 2023-09-15 | 上海航天空间技术有限公司 | Satellite data real-time transmission method and system for remote sensing monitoring of small-area mountain fire |
| CN116760456B (en) * | 2023-08-14 | 2023-10-31 | 上海航天空间技术有限公司 | Satellite data real-time transmission method and system for remote sensing monitoring of small-area mountain fire |
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