A method and device for multi-satellite transit prediction

Abstract

The present invention provides a multi-satellite transit prediction method and device, belonging to the field of satellite remote sensing technology, wherein the multi-satellite transit prediction method includes: obtaining observation information; obtaining the operation information of each target satellite in a target time period; dividing the shooting area of ​​the target satellite's operating position at any time into an east area and a west area according to the operation information; traversing the swing angle range of the target satellite with a preset swing angle step, determining the transit situation of the target satellite according to the intersection of the east area and the west area with the target area after each swing with the preset swing angle step, traversing the target time period with a preset time step, repeating the process of traversing the swing angle range of the target satellite with the preset swing angle step; generating a transit prediction result according to the transit situation of each target satellite. The multi-satellite transit prediction method in the present invention can support multi-satellite transit prediction, and the calculation efficiency is improved, and the accuracy of transit prediction is improved.

Description

Technical Field

[0001] The present invention relates to the field of satellite remote sensing technology, and in particular to a multi-satellite transit prediction method and device. Background Art

[0002] With the launch of more and more commercial remote sensing satellites, rich remote sensing data can be applied to more and more industries. Industry users generally have two data needs: archived data and programming data. Archived data is historical shooting data that intersects with the target area and is retrieved through spatial conditions. Programming data is the satellite's shooting data of the target area in a certain time period in the future that meets the user's resolution, coverage and other requirements. Programming data is more valuable, as it represents the future monitoring capabilities of a specific area, so the unit price is also higher than archived data. Therefore, it is more efficient and accurate to obtain which satellites will pass through the target area in the future time period, which can assist satellite operation and control personnel in generating satellite imaging plans, improve the efficiency of arranging programming data production, and increase the data revenue of satellite operators. Previous satellite transit prediction technologies usually target a single satellite, and the prediction accuracy is not high. Summary of the invention

[0003] In view of this, the present invention provides a multi-satellite transit prediction method and device, which are used to solve the problem that it is currently impossible to predict the transit of multiple satellites and the prediction accuracy is not high.

[0004] In order to solve the above technical problems, in a first aspect, the present invention provides a multi-satellite transit prediction method, the method comprising:

[0005] Acquiring observation information, wherein the observation information includes geographic space information of the observation target, target satellite information, and target time period;

[0006] According to the LTE data and the SGP4 model, the operation information of each target satellite in the target satellite information within the target time period is obtained;

[0007] According to the operation information, a shooting area of ​​the operation position of any target satellite at any time within the target time period is divided into an east area and a west area, wherein the east area is an area that can be shot by the target satellite when it swings to the east, and the west area is an area that can be shot by the target satellite when it swings to the west;

[0008] Traversing the swing angle range of the target satellite with a preset swing angle step, determining the transit of the target satellite according to the intersection of the east region and the west region with the target region after each swing with the preset swing angle step, traversing the target time period with a preset time step, and repeating the process of traversing the swing angle range of the target satellite with the preset swing angle step, wherein the target region is determined according to the geographic space information of the observed target;

[0009] A transit forecast result is generated according to the transit conditions of each of the target satellites.

[0010] Optionally, before the step of traversing the roll angle range of the target satellite with a preset roll angle step size, the method further includes:

[0011] Determining the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite;

[0012] When the target satellite is a radar satellite, the eastward swing angle range of the target satellite is determined to be , the swing angle range to the west is ;

[0013] When the target satellite is an optical satellite, the eastward swing angle range of the target satellite is determined to be from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

[0014] Optionally, the step of traversing the roll angle range of the target satellite with a preset roll angle step length, and determining the transit condition of the target satellite according to the intersection of the east region and the west region with the target region after each roll by the preset roll angle step length comprises:

[0015] If any one of the east area and the west area intersects with the target area, and the target satellite has no transit record under the current orbit circle number, it is confirmed that the target satellite transits the target area once, and the corresponding transit shooting area range, transit time, roll angle and roll direction are obtained;

[0016] If any one of the east region and the west region does not intersect with the target region, it is confirmed that the target satellite has not passed through the target region, and the side swing angle range of the target satellite is continuously traversed until the traversal is completed.

[0017] Optionally, the transit forecast result includes the transit information of each target satellite, the total number of transits, the shooting area and the shooting coverage rate, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the roll angle and the roll direction, the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area, and the shooting coverage rate is the ratio of the shooting area to the total area of ​​the target area.

[0018] Optionally, the step of generating a transit forecast result according to the transit conditions of each of the target satellites includes:

[0019] Taking the union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range;

[0020] Taking the intersection of the theoretical effective shooting range and the target area to obtain a shootable area;

[0021] The shooting coverage is obtained by dividing the area of ​​the shootable area by the total area of ​​the target area.

[0022] In a second aspect, the present invention further provides a multi-satellite transit prediction device, the device comprising:

[0023] A first acquisition module is used to acquire observation information, wherein the observation information includes geographic space information of the observation target, target satellite information and target time period;

[0024] A second acquisition module is used to acquire the operation information of each target satellite in the target time period according to the LTE data and the SGP4 model;

[0025] A division module, used for dividing the shooting area of ​​the running position of any target satellite at any time in the target time period into an east area and a west area according to the running information, wherein the east area is an area that can be shot by the target satellite when it swings to the east, and the west area is an area that can be shot by the target satellite when it swings to the west;

[0026] A traversal module is used to traverse the swing angle range of the target satellite with a preset swing angle step length, determine the transit situation of the target satellite according to the intersection of the east area and the west area with the target area after each swing with the preset swing angle step length, and traverse the target time period with a preset time step length, and repeat the process of traversing the swing angle range of the target satellite with the preset swing angle step length, wherein the target area is determined according to the geographic space information of the observation target;

[0027] The prediction module is used to generate a transit prediction result according to the transit conditions of each target satellite.

[0028] Optionally, the device further comprises:

[0029] A type determination module, used to determine the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite;

[0030] The first angle determination module is used to determine the eastward swing angle range of the target satellite when the target satellite is a radar satellite. , the swing angle range to the west is ;

[0031] The second angle determination module is used to determine, when the target satellite is an optical satellite, that the eastward swing angle range of the target satellite is from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

[0032] Optionally, the traversal module includes:

[0033] an intersection unit, configured to confirm that the target satellite passes through the target area once, and obtain the corresponding transit shooting area range, transit time, roll angle and roll direction when passing through, if any one of the east area and the west area intersects with the target area and the target satellite has no transit record under the current orbit circle number;

[0034] The non-intersecting unit is used to confirm that the target satellite has not passed through the target area if any one of the east area and the west area does not intersect with the target area, and continue to traverse the side swing angle range of the target satellite until the traversal is completed.

[0035] Optionally, the transit forecast result includes the transit information of each target satellite, the total number of transits, the shooting area and the shooting coverage rate, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the roll angle and the roll direction, the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area, and the shooting coverage rate is the ratio of the shooting area to the total area of ​​the target area.

[0036] Optionally, the prediction module includes:

[0037] A first calculation unit is used to obtain a union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range;

[0038] A second calculation unit is used to obtain a photographable area by taking the intersection of the theoretical effective shooting range and the target area;

[0039] The third calculation unit is used to divide the area of ​​the photographable area by the total area of ​​the target area to obtain the shooting coverage rate.

[0040] The beneficial effects of the above technical solution of the present invention are as follows:

[0041] In the embodiment of the present invention, multi-satellite transit prediction can be supported, the calculation process supports parameter information of multiple satellites, the calculation conditions take into account the sway parameters of the satellite in actual operation, and the satellite orbit prediction calculation is performed using TLE data and the SGP4 model. Forecasts within a short time period are supported, so the latest TLE data of the target satellite is automatically and regularly obtained and updated to ensure the accuracy of the calculation. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 Schematic diagram of a flow chart of a multi-satellite transit prediction method in Embodiment 1 of the present invention;

[0043] Figure 2 Schematic diagram of the relative positions of the side-swing shooting area and the target area of ​​the optical satellite in the first embodiment of the present invention;

[0044] Figure 3 Schematic diagram of the relative positions of the side-swing shooting area and the target area of ​​the radar satellite in the first embodiment of the present invention;

[0045] Figure 4 The figure is a schematic diagram of the structure of a multi-satellite transit prediction device in the second embodiment of the present invention. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solution and advantages of the embodiment of the present invention clearer, the technical solution of the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings of the embodiment of the present invention. Obviously, the described embodiment is a part of the embodiment of the present invention, not all of the embodiments. Based on the described embodiment of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present invention.

[0047] With the launch of more and more commercial remote sensing satellites, rich remote sensing data can be applied to more and more industries. Industry users generally have two data needs: archived data and programming data. Archived data is historical shooting data that intersects with the target area and is retrieved through spatial conditions. Programming data is the shooting data of the target area by satellite in a certain time period in the future that meets the user's requirements for resolution, coverage, etc. Programming data is more valuable. It represents the monitoring capability of a specific area in the future, so the unit price is also higher than archived data. Therefore, it is more efficient and accurate to obtain which satellites will pass through the target area in the future time period, which can assist satellite operation and control personnel in generating satellite imaging plans, improve the efficiency of arranging programming data production, and increase the data revenue of satellite operators. Previous satellite transit prediction technologies are usually aimed at single satellites, but there is currently no mature solution for transit forecast analysis of multiple satellites for target areas, especially for transit prediction combined with side swing conditions in actual satellite operation and control work.

[0048] Therefore, please refer to Figure 1 , Figure 1 A schematic flow chart of a multi-satellite transit prediction method provided in Embodiment 1 of the present invention, the method comprising the following steps:

[0049] Step 11: Acquire observation information, which includes geographic space information of the observation target, target satellite information and target time period.

[0050] In this embodiment, the observation target supports online retrieval of POI (Point Of Interest), AOI (Area of ​​Interest), and acquisition by uploading vector files, and its data format can be a GeoJSON object, that is, online retrieval can be performed to obtain the observation target by uploading data files. Among them, GeoJSON is a format for encoding various geographic data structures, and is a geographic spatial information data exchange format based on JavaScript Object Notation (JSON). GeoJSON objects can represent geometry, features, or feature sets.

[0051] In this embodiment, the target satellite information includes the number and type of target satellites, and specifically, it can support the acquisition of more than 30 satellites in the series of high-resolution, environment, resource, land detection, 4D high-view, high-view, sentinel, land, etc. The types of target satellites include optical satellites, radar satellites, etc.

[0052] The target time period is the observation time, i.e. the forecast time, which can specifically support time periods such as the next day, the next three days, the next week, and customized time periods within the next week.

[0053] Step 12: According to the LTE data and the SGP4 model, the operation information of each target satellite in the target satellite information within the target time period is obtained.

[0054] In this step, the motion information of each target satellite in the target time period is obtained based on TLE data and SGP4 model. This motion information includes: longitude and latitude of the sub-satellite point, motion direction, motion speed, altitude, number of orbits, etc. Among them, the two-line orbital data (TLE, Two-Line Orbital Element) determines the time, coordinates, orientation, speed and other parameters of the flying body based on the mathematical relationship between the six orbital parameters of Kepler's law, with extremely high accuracy; SGP4 (Simplified General Perturbations 4) is a mathematical model used to predict the position of low-Earth orbit satellites.

[0055] If the TLE data of the target satellite is included in CelesTrak, access and automatic update are supported. CelesTrak is a non-profit organization dedicated to providing orbital data of space objects. Its main mission is to make data and other resources free and open to the space community to promote the understanding and safe and responsible use of the orbital environment. CelesTrak pays special attention to the release and maintenance of satellite ephemeris. Satellite orbit prediction calculations are performed using TLE data and the SGP4 model, supporting predictions within a short period of time. Therefore, the latest TLE data of the target satellite is automatically and regularly obtained and updated to ensure the accuracy of the calculation.

[0056] Step 13: According to the operation information, the shooting area of ​​the operating position of any target satellite at any time within the target time period is divided into an east area and a west area, the east area is the area that can be photographed by the target satellite when it swings to the east, and the west area is the area that can be photographed by the target satellite when it swings to the west.

[0057] According to the operation information obtained in the above steps, when the target satellite moves to a certain position at a certain time, the shooting area of ​​the target satellite can be divided into two areas, the east area and the west area, where the east area is the area that can be photographed by the target satellite swinging to the east, and the west area is the area that can be photographed by the target satellite swinging to the west. In other words, the east area is the area covered by the highest longitude corresponding to the maximum side swing to the east to the minimum longitude corresponding to the subsatellite point, and the west area is the area covered by the lowest longitude corresponding to the maximum side swing to the west to the highest longitude corresponding to the subsatellite point. The east / west area is a dynamic area, and the shooting range after the side swing is different depending on the position of the target satellite.

[0058] Step 14: traverse the swing angle range of the target satellite with a preset swing angle step, determine the transit situation of the target satellite according to the intersection of the east area and the west area with the target area after each swing with the preset swing angle step, traverse the target time period with a preset time step, and repeat the process of traversing the swing angle range of the target satellite with a preset swing angle step, wherein the target area is determined based on the geographic spatial information of the observed target.

[0059] In this embodiment, each target satellite has its corresponding roll angle range. When the target satellite moves to a certain position at a certain moment in the target time period, the roll angle range can be used as a boundary and a preset roll angle as a step length to traverse the roll angle range, traverse and calculate the dynamic changes of the east region and the west region, and determine whether the east region and the west region under the corresponding roll angle intersect with the target region, and then determine the transit of the target satellite. Since the above roll angle traversal process is at a certain fixed moment, in order to achieve the prediction within the target time period, it is necessary to further traverse the target time period with a preset time step length, and repeat the above process of traversing the roll angle range of the target satellite with the preset roll angle step length, that is, after each preset time step length, perform a roll angle traversal, traverse and calculate the dynamic changes of the corresponding east region and west region, and determine whether the east region and the west region under the corresponding roll angle intersect with the target region, and then determine the transit of the target satellite.

[0060] In this step, the target area is determined based on the geographic space information of the observation target in the observation information obtained in the previous step.

[0061] The off-nadir angle of the target satellite mainly involves two key parameters: the off-nadir angle and the elevation angle. The off-nadir angle refers to the offset angle of the satellite sensor relative to the positive vertical direction. When collecting satellite images, the satellite sensor always has a certain degree of inclination when collecting images. This inclination is usually expressed by the off-nadir angle; the elevation angle refers to the angle between the satellite sensor and the vertical direction of the ground.

[0062] In some embodiments, optionally, the preset side swing angle step is 0.1° and the preset time step is 1000 milliseconds.

[0063] In this embodiment, the calculation conditions take into account the roll parameters of the target satellite in actual operation and control, which can effectively improve the accuracy of the prediction.

[0064] Step 15: Generate a transit forecast result according to the transit conditions of each target satellite.

[0065] After obtaining the corresponding calculation results / transit conditions in the aforementioned steps, the transit forecast results of multiple satellites can be generated accordingly to assist satellite operation and control personnel in generating satellite imaging plans and improve the efficiency of arranging programming data production.

[0066] The multi-satellite transit prediction method provided by the embodiment of the present invention can support multi-satellite transit prediction. The calculation process supports parameter information of multiple satellites. The calculation conditions take into account the sway parameters of the satellites in actual operation. The satellite orbit prediction calculation is performed using TLE data and the SGP4 model. The prediction within a short time period is supported. Therefore, the latest TLE data of the target satellite is automatically and regularly obtained and updated to ensure the accuracy of the calculation.

[0067] The following example illustrates the above-mentioned multi-satellite transit prediction method.

[0068] In one optional specific implementation manner, before the step of traversing the roll angle range of the target satellite with a preset roll angle step size, the method further includes:

[0069] Determining the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite;

[0070] When the target satellite is a radar satellite, the eastward swing angle range of the target satellite is determined to be , the swing angle range to the west is ;

[0071] When the target satellite is an optical satellite, the eastward swing angle range of the target satellite is determined to be from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

[0072] In this embodiment, the east region represents the maximum area that can be photographed when the target satellite moves to a certain position and swings to the east. It is a dynamic value. The photographable range after the swing is different for different positions of the target satellite, and the same is true for the west region. Therefore, before traversing the swing angle range of the target satellite with a preset swing angle step, it is necessary to first determine the swing angle range of the target satellite.

[0073] Specifically, the type of the target satellite is first determined based on the target satellite information. If the target satellite is a radar satellite, since the radar satellite cannot capture the sub-satellite position, the side swing angle range of the radar satellite can be limited based on general data. For example, the side swing angle range of the radar satellite can be limited to , that is, the swing angle range to the east is , the swing angle range to the west is If the target satellite is an optical satellite, it is determined according to the maximum swing angle supported by the target satellite itself, that is, the eastward swing angle range of the target satellite is from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the subsatellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the subsatellite point.

[0074] Please refer to Figure 2 and Figure 3 , Figure 2 A schematic diagram of the relative positions of the side-swing shooting area and the target area of ​​the optical satellite provided in the first embodiment of the present invention, Figure 3 A schematic diagram of the relative positions of the side-swing shooting area and the target area of ​​the radar satellite provided in Embodiment 1 of the present invention.

[0075] In some embodiments of the present application, the step of traversing the roll angle range of the target satellite with a preset roll angle step length, and determining the transit condition of the target satellite according to the intersection of the east region and the west region with the target region after each roll by the preset roll angle step length comprises:

[0076] If any one of the east area and the west area intersects with the target area, and the target satellite has no transit record under the current orbit circle number, it is confirmed that the target satellite transits the target area once, and the corresponding transit shooting area range, transit time, roll angle and roll direction are obtained;

[0077] If any one of the east region and the west region does not intersect with the target region, it is confirmed that the target satellite has not passed through the target region, and the side swing angle range of the target satellite is continuously traversed until the traversal is completed.

[0078] In this embodiment, taking the target satellite as an optical satellite as an example, starting from the subsatellite point position, taking the maximum roll angle of the target satellite as the boundary, taking the roll angle of 0.1° as the step length, traversing and calculating the dynamic changes of the east / west area, and judging the intersection of the east and west areas with the target area, if there is an intersection and there is no transit record under the current orbit number, then it is considered that the target satellite passes through the target area once, if there is no intersection, then continue to calculate until the roll angle exceeds the limit range. After completing the roll traversal, continue to repeat the above steps with a time step of 1000 milliseconds until the calculation time exceeds the aforementioned target time period.

[0079] In this embodiment, there is logic for deduplicating the number of target satellite transits. Specifically, during the process of the target satellite moving around the earth once, it may have multiple transits. In this method, only the first transit is recorded, and the subsequent transit results of this circle are discarded, that is, repeated transits on the same track are pruned, which effectively improves the calculation efficiency compared with the traditional exhaustive method. In other words, only when any one of the east and west regions intersects with the target region and the target satellite has no transit record under the current orbital number of circles, a transit record is made, and the subsequent transits of this circle are no longer recorded.

[0080] When judging the intersection of either the east region or the west region with the target region (i.e., whether they intersect), the Turf tool can be used for auxiliary judgment. Turf.js is a powerful JavaScript geospatial analysis library for processing vector data in geographic information systems. It focuses on providing lightweight, modern geospatial tools suitable for use in browsers and Node.js environments. Turf.js is often used in Web-based map applications for real-time geographic data calculation and visualization. Therefore, judging the geographical location relationship between either the east region or the west region and the target region avoids the situation in which the traditional satellite transit forecast calculation simplifies the target region into the minimum enclosing rectangle. After adding the buffer zone, the calculation result will show that the shooting strip area and the target area do not intersect, which improves the accuracy of the transit forecast.

[0081] In this embodiment, since any one of the east area and the west area intersects with the target area and the target satellite has no transit record under the current number of orbital circles, it is considered that the target satellite transits the target area once, and then the corresponding information such as the transit shooting area range, transit time, roll angle and roll direction can be obtained at this time, so as to complete the transit forecast calculation of a single target satellite, and the transit forecast calculation results of each target satellite are combined to obtain the transit forecast results of multiple satellites.

[0082] In some other embodiments of the present application, the transit forecast results include the transit information, total transit times, shooting area and shooting coverage of each of the target satellites, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the swing angle and the swing direction, the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area, and the shooting coverage is the ratio of the shooting area to the total area of ​​the target area.

[0083] In some embodiments, the step of generating a transit forecast result according to the transit conditions of each of the target satellites includes:

[0084] Taking the union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range;

[0085] Taking the intersection of the theoretical effective shooting range and the target area to obtain a shootable area;

[0086] The shooting coverage is obtained by dividing the area of ​​the shootable area by the total area of ​​the target area.

[0087] Specifically, this embodiment merges the transit shooting area ranges of all target satellites, that is, takes the union, to obtain the theoretical effective shooting range of this forecast, and takes the intersection of this theoretical effective shooting range and the target area to obtain the shootable area of ​​the target satellite. The area of ​​the shootable area is the shooting area, and the area of ​​the shootable area divided by the total area of ​​the target area is the shooting coverage rate.

[0088] In this way, all the required information in the transit forecast results can be obtained, including the transit information of each target satellite, the total number of transits, the shooting area, the shooting coverage rate, etc.

[0089] In some embodiments of the present invention, it is optionally possible to support the separate generation of transit information of optical satellites and radar satellites, including the number of transits, shooting areas, shooting coverage, etc. of optical satellites and radar satellites, respectively, so as to distinguish between optical satellites and radar satellites.

[0090] The embodiments of the present invention have the following effects:

[0091] (1) Support for multi-satellite transit prediction: The calculation process supports parameter information of multiple satellites. The calculation conditions take into account the sway parameters of the satellite in actual operation and control work. It also supports the expansion of satellite information. If the satellite's TLE data is included in CelesTrak, it supports access and automatic update.

[0092] (2) Improved computing efficiency: The calculation process is pruned based on the satellite’s spectral characteristics and repeated transits on the same track, which effectively improves computing efficiency compared to the traditional exhaustive method.

[0093] (3) Improved accuracy of transit forecasts: Satellite orbit forecast calculations are performed using TLE data and the SGP4 model, which only supports forecasts within a short period of time. Therefore, the latest TLE of the target satellite is automatically updated at regular intervals to ensure the accuracy of the calculations. At the same time, traditional satellite transit forecast calculations simplify the target area into a minimum bounding rectangle. After adding a buffer zone, the calculation results show that the shooting strip area and the target area do not intersect. The present invention uses the Turf tool to determine the geographical location relationship between the actual target area and the shooting strip, avoiding this situation and improving the accuracy of transit forecasts.

[0094] In summary, the multi-satellite transit prediction technology based on the SGP4 model can efficiently and accurately obtain satellite transit information in the target area in the future time period, assist satellite operation and control personnel in generating satellite imaging plans, and improve the efficiency of arranging programming data production.

[0095] See also Figure 4 , Figure 4 : is a schematic diagram of the structure of a multi-satellite transit prediction device provided by Embodiment 2 of the present invention, the device 50 comprises:

[0096] A first acquisition module 51 is used to acquire observation information, wherein the observation information includes geographic space information of the observation target, target satellite information and target time period;

[0097] A second acquisition module 52 is used to acquire the operation information of each target satellite in the target time period according to the LTE data and the SGP4 model;

[0098] A division module 53 is used to divide the shooting area of ​​the running position of any target satellite at any time in the target time period into an east area and a west area according to the running information, wherein the east area is an area that can be shot by the target satellite when it swings to the east, and the west area is an area that can be shot by the target satellite when it swings to the west;

[0099] A traversal module 54 is used to traverse the swing angle range of the target satellite with a preset swing angle step length, determine the transit situation of the target satellite according to the intersection of the east area and the west area with the target area after each swing with the preset swing angle step length, and traverse the target time period with a preset time step length, and repeat the process of traversing the swing angle range of the target satellite with the preset swing angle step length, wherein the target area is determined according to the geographic space information of the observation target;

[0100] The prediction module 55 is used to generate a transit prediction result according to the transit conditions of each target satellite.

[0101] Optionally, the device further comprises:

[0102] A type determination module, used to determine the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite;

[0103] The first angle determination module is used to determine the eastward swing angle range of the target satellite when the target satellite is a radar satellite. , the swing angle range to the west is ;

[0104] The second angle determination module is used to determine, when the target satellite is an optical satellite, that the eastward swing angle range of the target satellite is from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

[0105] Optionally, the traversal module includes:

[0106] an intersection unit, configured to confirm that the target satellite passes through the target area once, and obtain the corresponding transit shooting area range, transit time, roll angle and roll direction when passing through, if any one of the east area and the west area intersects with the target area and the target satellite has no transit record under the current orbit circle number;

[0107] The non-intersecting unit is used to confirm that the target satellite has not passed through the target area if any one of the east area and the west area does not intersect with the target area, and continue to traverse the side swing angle range of the target satellite until the traversal is completed.

[0108] Optionally, the transit forecast result includes the transit information of each target satellite, the total number of transits, the shooting area and the shooting coverage rate, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the roll angle and the roll direction, the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area, and the shooting coverage rate is the ratio of the shooting area to the total area of ​​the target area.

[0109] Optionally, the prediction module includes:

[0110] A first calculation unit is used to obtain a union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range;

[0111] A second calculation unit is used to obtain a photographable area by taking the intersection of the theoretical effective shooting range and the target area;

[0112] The third calculation unit is used to divide the area of ​​the photographable area by the total area of ​​the target area to obtain the shooting coverage rate.

[0113] In an embodiment of the present invention, multi-satellite transit prediction can be supported, the calculation process supports parameter information of multiple satellites, the calculation conditions take into account the sway parameters of the satellite in actual operation, and the satellite orbit prediction calculation is performed using TLE data and the SGP4 model. Only predictions within a short time period are supported, so the latest TLE data of the target satellite is automatically and regularly obtained and updated to ensure the accuracy of the calculation.

[0114] The embodiment of the present invention is a product embodiment corresponding to the above-mentioned method embodiment 1, so it will not be described in detail here. Please refer to the above-mentioned embodiment 1 for details.

[0115] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A multi-satellite transit prediction method, characterized in that: The method comprises the following steps: Acquiring observation information, wherein the observation information includes geographic space information of the observation target, target satellite information, and target time period; According to the LTE data and the SGP4 model, the operation information of each target satellite in the target satellite information within the target time period is obtained; According to the operation information, a shooting area of ​​the operation position of any target satellite at any time within the target time period is divided into an east area and a west area, wherein the east area is an area that can be shot by the target satellite when it swings to the east, and the west area is an area that can be shot by the target satellite when it swings to the west; Traversing the swing angle range of the target satellite with a preset swing angle step, determining the transit of the target satellite according to the intersection of the east region and the west region with the target region after each swing with the preset swing angle step, traversing the target time period with a preset time step, and repeating the process of traversing the swing angle range of the target satellite with the preset swing angle step, wherein the target region is determined according to the geographic space information of the observed target; A transit forecast result is generated according to the transit conditions of each of the target satellites.

2. The method according to claim 1, characterized in that: Before the step of traversing the roll angle range of the target satellite with a preset roll angle step size, the method further includes: Determining the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite; When the target satellite is a radar satellite, the eastward swing angle range of the target satellite is determined to be , the swing angle range to the west is ; When the target satellite is an optical satellite, the eastward swing angle range of the target satellite is determined to be from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

3. The method according to claim 1, characterized in that The step of traversing the roll angle range of the target satellite with a preset roll angle step length, and determining the transit condition of the target satellite according to the intersection of the east region and the west region with the target region after each roll by the preset roll angle step length comprises: If any one of the east area and the west area intersects with the target area, and the target satellite has no transit record under the current orbit circle number, it is confirmed that the target satellite transits the target area once, and the corresponding transit shooting area range, transit time, roll angle and roll direction are obtained; If any one of the east region and the west region does not intersect with the target region, it is confirmed that the target satellite has not passed through the target region, and the side swing angle range of the target satellite is continuously traversed until the traversal is completed.

4. The method according to claim 3, characterized in that: The transit forecast result includes the transit information, total transit times, shooting area and shooting coverage of each of the target satellites, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the roll angle and the roll direction; the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area; and the shooting coverage is the ratio of the shooting area to the total area of ​​the target area.

5. The method according to claim 4, characterized in that The step of generating a transit forecast result according to the transit conditions of each target satellite comprises: Taking the union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range; Taking the intersection of the theoretical effective shooting range and the target area to obtain a shootable area; The shooting coverage is obtained by dividing the area of ​​the shootable area by the total area of ​​the target area.

6. A multi-satellite transit prediction device, characterized in that: The device comprises: A first acquisition module is used to acquire observation information, wherein the observation information includes geographic space information of the observation target, target satellite information and target time period; A second acquisition module is used to acquire the operation information of each target satellite in the target time period according to the LTE data and the SGP4 model; A division module, used for dividing the shooting area of ​​the running position of any target satellite at any time in the target time period into an east area and a west area according to the running information, wherein the east area is an area that can be shot by the target satellite when it swings to the east, and the west area is an area that can be shot by the target satellite when it swings to the west; A traversal module is used to traverse the swing angle range of the target satellite with a preset swing angle step length, determine the transit situation of the target satellite according to the intersection of the east area and the west area with the target area after each swing with the preset swing angle step length, and traverse the target time period with a preset time step length, and repeat the process of traversing the swing angle range of the target satellite with the preset swing angle step length, wherein the target area is determined according to the geographic space information of the observation target; The prediction module is used to generate a transit prediction result according to the transit conditions of each target satellite.

7. The device according to claim 6, characterized in that The device also includes: A type determination module, used to determine the type of the target satellite according to the target satellite information, where the type of the target satellite includes a radar satellite and an optical satellite; The first angle determination module is used to determine the eastward swing angle range of the target satellite when the target satellite is a radar satellite. , the swing angle range to the west is ; The second angle determination module is used to determine, when the target satellite is an optical satellite, that the eastward swing angle range of the target satellite is from the maximum eastward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point, and the westward swing angle range is from the maximum westward swing angle supported by the target satellite to 0° corresponding to the sub-satellite point.

8. The device according to claim 6, characterized in that The traversal module includes: an intersection unit, configured to confirm that the target satellite passes through the target area once, and obtain the corresponding transit shooting area range, transit time, roll angle and roll direction when passing through, if any one of the east area and the west area intersects with the target area and the target satellite has no transit record under the current orbit circle number; The non-intersecting unit is used to confirm that the target satellite has not passed through the target area if any one of the east area and the west area does not intersect with the target area, and continue to traverse the side swing angle range of the target satellite until the traversal is completed.

9. The device according to claim 8, characterized in that The transit forecast result includes the transit information, total transit times, shooting area and shooting coverage of each of the target satellites, wherein the transit information includes the longitude and latitude of the sub-satellite point, the transit time, the roll angle and the roll direction; the shooting area is the area of ​​the shootable area of ​​all the target satellites on the target area; and the shooting coverage is the ratio of the shooting area to the total area of ​​the target area.

10. The device according to claim 9, characterized in that The prediction module comprises: A first calculation unit is used to obtain a union of the transit shooting area ranges of all the target satellites to obtain a theoretical effective shooting range; A second calculation unit is used to obtain a photographable area by taking the intersection of the theoretical effective shooting range and the target area; The third calculation unit is used to divide the area of ​​the photographable area by the total area of ​​the target area to obtain the shooting coverage rate.

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