Numerical simulation evaluation method, device and equipment for satellite imaging coverage capability

Abstract

The invention provides a numerical simulation evaluation method, device and equipment for satellite imaging coverage capability, and relates to the technical field of spaceflight, and the method comprises the steps: carrying out orbit recursion to generate an initial orbit sequence of a satellite; performing visibility screening on the initial orbit sequence according to the center ground distance of each wave position of the load and the geographical boundary point set to obtain a transit orbit sequence; determining a transit map corresponding to each transit orbit sequence, and performing operation blocking in the transit map corresponding to each transit orbit sequence in a grid division form according to the load wave position size and the load coverage overlapping rate to obtain an imaging array of each transit of the satellite; and by taking the regression cycle number as an outer layer cycle and the transit serial number as an inner layer cycle, carrying out cycle evaluation on whether the imaging array of the transit of the satellite at each time can be imaged, and determining a target regression cycle number until the imaging array is completely covered. According to the method, the accuracy of a calculation result is effectively improved, and the more refined analysis requirement in actual work is met.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular, to a numerical simulation evaluation method, device and equipment for satellite imaging coverage capability. Background Art

[0002] In satellite design and application practice, the imaging coverage capability of a specified ground area has received extensive attention from satellite users. Generally, users hope to know the time required for a satellite to complete a complete image of a specified target area. Limited by the field of view width of the satellite payload, the area that can be imaged by the satellite during a single pass over the target area is only a very small part of the entire target area. Therefore, the satellite needs to pass over the orbit multiple times to splice into a complete image. For the calculation of the total duration, the simple estimation method generally has conservative assumptions, resulting in uncertain calculation results. Summary of the Invention

[0003] In view of this, the purpose of the present invention is to provide a numerical simulation evaluation method, device and equipment for satellite imaging coverage capability, which effectively improves the accuracy of the calculation results and meets the more refined analysis requirements in actual work.

[0004] In a first aspect, the present invention provides a numerical simulation evaluation method for satellite imaging coverage capability, including:

[0005] Obtain the payload wave position configuration parameters of the satellite, and obtain the set of geographical boundary points of multiple independent geographical regions. The payload wave position configuration parameters include the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate;

[0006] Based on the epoch orbit elements of the satellite, perform orbit recursion according to the forecast duration and the specified time interval to generate the initial orbit sequence of the satellite, and perform visibility screening on the initial orbit sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminate the orbit sequences that are necessarily unable to photograph the independent geographical region to obtain the transit orbit sequence;

[0007] Obtain the transit map corresponding to each transit orbit sequence by performing coordinate system conversion on the set of geographical boundary points, and perform operation partitioning in the form of grid division in the transit map corresponding to each transit orbit sequence according to the payload wave position size and the payload coverage overlap rate to obtain the imaging array for each satellite transit;

[0008] Take the number of regression cycles as the outer loop and the transit serial number as the inner loop, and perform a loop evaluation on whether the imaging array for each satellite transit can be imaged until the imaging array is completely covered, and determine the target regression cycle number of the satellite based on the cumulative number of times of the outer loop.

[0009] In one embodiment, visibility screening is performed on the initial orbit sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and the orbit sequences that are necessarily unable to photograph an independent geographical area are excluded to obtain the transit orbit sequences, including:

[0010] According to the set of geographical boundary points and the imaging flags carried by each initial single-orbit sequence corresponding to each orbit number in the initial orbit sequence, intermediate single-orbit sequences are screened. The imaging flags include ascending orbit imaging flags or descending orbit imaging flags;

[0011] The position of each point in the set of geographical boundary points is successively converted into the satellite's orbital coordinate system to obtain the set of converted geographical boundary points corresponding to each intermediate single-orbit sequence, and the minimum extreme point and the maximum extreme point are extracted from the set of converted geographical boundary points in a specified orientation;

[0012] Based on preset screening conditions, the orbit sequences that are necessarily unable to photograph an independent geographical area are excluded to obtain the transit orbit sequences. The preset screening conditions include: the Z component of the position of the first point in the set of geographical boundary points is greater than the radius of the earth, and the minimum extreme point is greater than the maximum value of the central ground distance of each wave position of the payload, and the maximum extreme point is less than the minimum value of the central ground distance of each wave position of the payload.

[0013] In one embodiment, according to the payload wave position size and the payload coverage overlap rate, operation blocks are performed in the form of grid division in the transit map corresponding to each transit orbit sequence to obtain the imaging array for each satellite transit, including:

[0014] According to the azimuth size in the payload wave position size and the payload coverage overlap rate, the number of rows of the imaging array is determined based on the distance scale in the longitudinal direction of the entire transit map;

[0015] In the transit map corresponding to each transit orbit sequence, based on the number of rows of the imaging array, the row imaging array is determined based on the distance scale in the transverse direction of the transit map;

[0016] After the row imaging arrays are translated left and right, the union of the row imaging arrays corresponding to the same row in the entire transit map is obtained to obtain the imaging array for each satellite transit.

[0017] In one embodiment, the imaging array is a plurality of imaging intervals that are longitudinally discrete and transversely continuous.

[0018] In one embodiment, with the number of regression cycles as the outer loop and the transit sequence number as the inner loop, a loop evaluation of whether imaging is possible is performed on the imaging array for each satellite transit. Until the imaging array is completely covered, the target regression cycle number of the satellite is determined based on the cumulative number of times of the outer loop, including:

[0019] For each transit serial number within the current regression cycle, sequentially evaluate whether imaging is possible, and update the current imaging array to obtain a new current imaging array;

[0020] Continue to sequentially evaluate whether imaging is possible for each transit serial number within the next regression cycle, and update the current imaging array to obtain a new current imaging array. When the imaging array is completely covered, use the cumulative number of outer loops as the target regression cycle number of the satellite.

[0021] In one implementation, for each transit serial number within the current regression cycle, sequentially evaluate whether imaging is possible, and update the current imaging array to obtain a new current imaging array, including:

[0022] For the current transit serial number within the current regression cycle, for the imaging array corresponding to any combination of the wave position number and the imaging array row number in the current imaging array, if it is determined that the imaging array corresponding to this combination is capable of imaging according to the range dimension in the payload wave position size, then take this combination as the alternative imaging strategy corresponding to the current transit serial number, and randomly determine the target imaging strategy corresponding to the current transit serial number from the alternative imaging strategies corresponding to the current transit serial number;

[0023] Update the imaging array based on the target imaging strategy to obtain a new current imaging array;

[0024] Continue to determine the target imaging strategy corresponding to the next transit serial number within the current regression cycle until the target imaging strategies corresponding to each transit serial number within the current regression cycle are determined, and then update the current imaging array again according to the target imaging strategy corresponding to the last transit serial number within the current regression cycle to obtain a new current imaging array.

[0025] In one implementation, updating the current imaging array based on the target imaging strategy to obtain a new current imaging array includes:

[0026] Update the current imaging array according to the following formula:

[0027]

[0028] where, is the new current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy; is the current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy, A and B are intermediate parameters, S nsel is the central ground distance of the selected wave position number nsel in the target imaging strategy, H R is the range dimension in the payload wave position size.

[0029] In a second aspect, the present invention further provides a numerical simulation evaluation device for satellite imaging coverage ability, including:

[0030] A data acquisition module, configured to acquire the load wave position configuration parameters of the satellite and the set of geographical boundary points of multiple independent geographical regions. The load wave position configuration parameters include the central ground distance of each load wave position, the load wave position size, and the load coverage overlap rate;

[0031] A transit orbit sequence determination module, configured to perform orbit recursion based on the epoch orbit elements of the satellite according to the prediction duration and the specified time interval to generate the initial orbit sequence of the satellite, and perform visibility screening on the initial orbit sequence according to the central ground distance of each load wave position and the set of geographical boundary points, and eliminate the orbit sequences that are necessarily unable to photograph the independent geographical regions to obtain the transit orbit sequence;

[0032] An imaging array division module, configured to obtain the transit map corresponding to each transit orbit sequence by performing coordinate system conversion on the set of geographical boundary points, and perform operation block division in the form of grid division in the transit map corresponding to each transit orbit sequence according to the load wave position size and the load coverage overlap rate to obtain the imaging array for each satellite transit;

[0033] A loop evaluation module, configured to perform a loop evaluation on whether the imaging array for each satellite transit can be imaged with the number of regression cycles as the outer loop and the transit sequence number as the inner loop, and when the imaging array is completely covered, determine the target regression cycle number of the satellite based on the cumulative number of times of the outer loop.

[0034] In a third aspect, the present invention further provides an electronic device, including a processor and a memory. The memory stores computer executable instructions that can be executed by the processor, and the processor executes the computer executable instructions to implement the method according to any one of the first aspect.

[0035] In a fourth aspect, the present invention further provides a computer-readable storage medium, which stores computer executable instructions. When the computer executable instructions are called and executed by the processor, the computer executable instructions cause the processor to implement the method according to any one of the first aspect.

[0036] A numerical simulation evaluation method, device and equipment for satellite imaging coverage ability provided by the present invention first obtains the payload wave position configuration parameters of the satellite and obtains the set of geographical boundary points of multiple independent geographical regions. The payload wave position configuration parameters include the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate. Then, based on the epoch orbital elements of the satellite, orbit recursion is performed according to the forecast duration and the specified time interval to generate the initial orbit sequence of the satellite, and the initial orbit sequence is screened for visibility according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and the orbit sequences that are necessarily unable to photograph the independent geographical regions are excluded to obtain the transit orbit sequence. Then, by performing coordinate system conversion on the set of geographical boundary points, the transit map corresponding to each transit orbit sequence is obtained, and according to the payload wave position size and the payload coverage overlap rate, the operation is divided into blocks in the form of grid division in the transit map corresponding to each transit orbit sequence to obtain the imaging array for each transit of the satellite. Finally, with the number of regression cycles as the outer loop and the transit serial number as the inner loop, a loop evaluation of whether imaging is possible is performed on the imaging array for each transit of the satellite until the imaging array is completely covered, and the target regression cycle number of the satellite is determined based on the cumulative number of times of the outer loop. The above method simulates the transit scenario of the satellite through simulation, divides the imaging array for a given geographical region, and based on the imaging strategy during each effective transit, completes the corresponding part of the imaging array until the imaging history covers the entire region, and outputs the target regression cycle number required for full-coverage imaging. The present invention is a good alternative to the simple estimation method of satellite imaging coverage ability, making up for the shortcoming of the uncertain credibility of the results of the simple evaluation method, and providing an important reference basis with practical value for satellite demonstration and business negotiation. On the other hand, the present invention is also an evaluation framework for a set of satellite imaging strategies, providing a quantitative analysis means for the execution efficiency of the imaging strategy and being an important cornerstone for the design and optimization of the imaging strategy.

[0037] Other features and advantages of the present invention will be described in the following specification, and in part will be obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention are achieved and obtained by the structures specifically pointed out in the specification, claims and drawings.

[0038] To make the above objectives, features and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given and described in detail in conjunction with the accompanying drawings. Description of the Drawings

[0039] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0040] Figure 1 Schematic flowchart of a numerical simulation evaluation method for satellite imaging coverage ability provided by an embodiment of the present invention;

[0041] Figure 2 Technical block diagram of a numerical simulation evaluation method for satellite imaging coverage ability provided by an embodiment of the present invention;

[0042] Figure 3 Schematic diagram of the screening of a transit orbit sequence provided by an embodiment of the present invention;

[0043] Figure 4 Schematic diagram of a transit map provided by an embodiment of the present invention;

[0044] Figure 5 Schematic diagram of the imaging array division for the first effective transit provided by an embodiment of the present invention;

[0045] Figure 6 Schematic diagram of the imaging array division for the second effective transit provided by an embodiment of the present invention;

[0046] Figure 7 Schematic diagram of the imaging array division for the third effective transit provided by an embodiment of the present invention;

[0047] Figure 8 Schematic diagram of the imaging array division for the fourth effective transit provided by an embodiment of the present invention;

[0048] Figure 9 Schematic diagram of the imaging array division for the fifth effective transit provided by an embodiment of the present invention;

[0049] Figure 10 Schematic diagram of the imaging array division for the sixth effective transit provided by an embodiment of the present invention;

[0050] Figure 11 Schematic diagram of the imaging array division for the seventh effective transit provided by an embodiment of the present invention;

[0051] Figure 12 Schematic diagram of the imaging array division provided by an embodiment of the present invention;

[0052] Figure 13It shows an instantaneous state of a cyclic process provided by an embodiment of the present invention;

[0053] Figure 14 It is a schematic structural diagram of a numerical simulation evaluation device for the satellite imaging coverage ability provided by an embodiment of the present invention;

[0054] Figure 15 It is a schematic structural diagram of an electronic device provided by an embodiment of the present invention. Specific implementation manners

[0055] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0056] Currently, for the calculation of the total duration of the satellite imaging coverage ability, existing simple estimation methods generally have conservative assumptions, resulting in uncertain calculation result deviations. Based on this, the embodiments of the present invention provide a numerical simulation evaluation method, device, and equipment for the satellite imaging coverage ability, effectively improving the accuracy of the calculation results and meeting the more refined analysis requirements in actual work.

[0057] To facilitate the understanding of this embodiment, first, a numerical simulation evaluation method for the satellite imaging coverage ability disclosed in the embodiments of the present invention will be introduced in detail. Refer to Figure 1 The flowchart of a numerical simulation evaluation method for the satellite imaging coverage ability shown, and this method mainly includes the following steps S102 to step S108:

[0058] Step S102, obtain the payload wave position configuration parameters of the satellite, and obtain the set of geographical boundary points of multiple independent geographical regions. The payload wave position configuration parameters include the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate.

[0059] Step S104, based on the epoch orbital elements of the satellite, perform orbit recursion according to the forecast duration and the specified time interval to generate the initial orbit sequence of the satellite, and perform visibility screening on the initial orbit sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminate the orbit sequences that are necessarily unable to photograph the independent geographical regions to obtain the transit orbit sequence.

[0060] Among them, the initial orbit sequence of the satellite is also the time series data of the position, velocity, and attitude matrix of the satellite in the inertial coordinate system, and the transit orbit sequence is also a partial orbit sequence that can image the independent geographical area in the vicinity of the independent geographical area and in terms of geometric visibility. In one example, the initial orbit sequence of the satellite can be obtained by performing orbit recurrence according to the standard J2 or J4 recurrence method, and then the initial orbit sequence is screened once according to the set of geographical boundary points to obtain an intermediate orbit sequence. Then, the intermediate orbit sequence is screened once according to the central ground distance of each carrier wave position and the set of geographical boundary points, and the necessarily invisible intermediate orbit sequence is removed, so as to obtain the transit orbit sequence.

[0061] Step S106: Obtain the transit map corresponding to each transit orbit sequence by performing coordinate transformation on the set of geographical boundary points, and perform operation partitioning in the form of grid partitioning in the transit map corresponding to each transit orbit sequence according to the load wave position size and the load coverage overlap rate, so as to obtain the imaging array for each satellite transit.

[0062] Among them, the transit map corresponding to the transit orbit sequence is also the boundary point data of the set of geographical boundary points transformed into the satellite coordinate system of the transit orbit sequence. The imaging array is the grid partitioning of the operation plan, where the vertical direction is a discrete partitioning and the horizontal direction is a continuous interval, that is, the imaging array is a plurality of imaging intervals that are vertically discrete and horizontally continuous. In one example, the position coordinates of each boundary point of each independent geographical area can be transformed into the satellite coordinate system, thereby obtaining the boundary point data in the satellite coordinate system corresponding to each transit orbit sequence, that is, the "transit map"; comprehensively considering the transit maps corresponding to all transit orbit sequences, the maximum number of imaging times required along the vertical direction is obtained according to the distance scale in the vertical direction, and it is defined as the number of rows of the imaging array; in the transit map corresponding to each transit orbit sequence, for each row of the imaging array, an imaging array corresponding to that row is generated according to the distance scale in the horizontal direction of the transit map corresponding to it; the imaging arrays corresponding to the transit maps of each time are translated left and right to a unified coordinate system in turn; for each row, the union of the array intervals corresponding to that row in all transit maps is obtained to obtain the imaging array for each satellite transit.

[0063] Step S108: Take the number of regression periods as the outer loop and the transit serial number as the inner loop, and perform a loop evaluation on whether the imaging array for each satellite transit can be imaged until the imaging array is completely covered, and determine the target regression period number of the satellite based on the cumulative number of times in the outer loop.

[0064] In one example, during each inner loop process, for the transit sequence numbers within the regression cycle count, it is necessary to determine the target imaging strategy corresponding to the current transit sequence number. After updating the current imaging array, determine the target imaging strategy corresponding to the next transit sequence number again until the target imaging strategies corresponding to each transit sequence number within the regression cycle count are obtained; during each outer loop process, for the regression cycle count, it is necessary to determine the target imaging strategies corresponding to each transit sequence number within the current regression cycle count, and update the current imaging array based on the target imaging strategies. The current imaging array is also the imaging area that has not been covered historically. Continue to determine the target imaging strategies corresponding to each transit sequence number within the next regression cycle count until the imaging array is completely covered; use the cumulative number of times of the outer loop as the target regression cycle count of the satellite.

[0065] The numerical simulation evaluation method for satellite imaging coverage ability provided by the embodiments of the present invention, through simulation, simulates the satellite transit scenario. For a given geographical area, an imaging array is divided. Based on the imaging strategy during each effective transit, the corresponding part of the imaging array is completed until the entire area is covered by the imaging history, and the target regression cycle count required for full coverage imaging is output. The embodiments of the present invention are a good alternative to the simple estimation method for satellite imaging coverage ability, making up for the shortcoming that the result credibility of the simple evaluation method is uncertain, and providing an important reference basis with practical value for satellite demonstration and business negotiation; on the other hand, the embodiments of the present invention are also an evaluation framework for a set of satellite imaging strategies, providing a quantitative analysis means for the execution efficiency of the imaging strategy, and being an important cornerstone for the design and optimization of the imaging strategy.

[0066] For ease of understanding, the embodiments of the present invention provide a specific implementation manner of the numerical simulation evaluation method for satellite imaging coverage ability. Refer to Figure 2 the technical block diagram of a numerical simulation evaluation method for satellite imaging coverage ability shown, which includes: a parameter setting link, a geographical area reading link, an orbit recursion link, a transit orbit segment screening link, a coordinate conversion link, an imaging array division link, an imaging strategy formulation link, an imaging array update link, and a result statistics link. Specifically:

[0067] Step 1, parameter setting link:

[0068] First, input calculation conditions, including orbit epoch, orbit parameters, regression days, regression orbits, satellite payload parameters, and other information required for scene setting.

[0069] In addition, it is also necessary to obtain the payload wave position configuration parameters, which can simulate the influence of key indicators in satellite engineering on the calculation results, including: the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate.

[0070] Specifically, set the central ground distance of each wave position of the payload: For a satellite payload with N wave positions, in the right-side imaging state, the central ground distance of each wave position is set to In the left-side imaging state, the central ground distance of each wave position is set to The unit is km. Define the set of central ground distances corresponding to each wave position of the payload in the left-side view and right-side view modes as:

[0071]

[0072] The corresponding wave position numbers are -N <,…, -1, 1, …, N in sequence. The central ground distance corresponding to wave position number n is denoted as S n .

[0073] Specifically, set the wave position size of the payload, including: the range dimension is denoted as H R , and the azimuth dimension is denoted as H A .

[0074] Specifically, set the payload coverage overlap rate, denoted as Overlap.

[0075] In addition, the ascending / descending orbit imaging flag should also be set. If only ascending orbit imaging is discussed, set it to "ascending orbit imaging"; if only descending orbit imaging is discussed, set it to "descending orbit imaging".

[0076] Step 2: Geographic area reading link: The input form is to read a geographic boundary file, and all the longitude and latitude data of the points contained in this geographic boundary file are used as the geographic boundary point set to support the real geographic area shape. This is different from the simplified solution that can only face simple area shapes.

[0077] In one example, the set of independent geographic areas can be read from the geographic boundary file, and the boundary point data is stored separately for each independent geographic area. Specifically, the set of independent geographic areas is stored in advance in the geographic boundary information file, that is, a.shp type file, and the standard function shaperead() provided by the Matlab ("Matrix Laboratory") platform is used for reading. Each independent individual in the set of independent geographic areas is stored in the form of a cell array, denoted as d is the independent individual number. When discussing the position coordinate set of the geographic area boundary points corresponding to a certain independent individual in the following text, it is abbreviated as

[0078] Step 3: Orbit recursion link: It can perform simulation calculations for multiple (unlimited number) non-connected geographic areas at one time.

[0079] In one example, based on the epoch orbital elements, orbital propagation can be performed according to the prediction duration and a specified time interval to generate time series data of the position, velocity, and attitude matrix of the satellite in the inertial system, and these data are stored in segments according to the orbit number. The data segmented by orbit are hereinafter collectively referred to as the "initial orbit sequence".

[0080] Among them, the inertial system is J2000; the input form of the satellite epoch orbit is the orbital elements; the position sequence is represented in rectangular coordinates.

[0081] Among them, for orbital propagation, orbital propagation is performed according to the standard J2 or J4 propagation method, and this is not elaborated in the embodiments of the present invention.

[0082] Step 4: Transit orbit segment screening link: Perform visibility screening on the "initial orbit sequence" to screen out the transit orbit sequence that is near the independent geographical area and can photograph the independent geographical area in terms of geometric visibility from the initial orbit sequence, and eliminate useless orbit segment data, such as Figure 3 As shown in a schematic diagram of screening a transit orbit sequence.

[0083] The embodiments of the present invention provide a specific implementation manner of the transit orbit segment screening link, see the following steps 4.1 to step 4.3:

[0084] Step 4.1, according to the set of geographical boundary points and the imaging flags carried by each initial single-orbit sequence corresponding to each orbit number in the initial orbit sequence, screen the intermediate single-orbit sequences, and the imaging flags include the ascending orbit imaging flag or the descending orbit imaging flag.

[0085] In a specific implementation manner, for the orbit segment data (hereinafter referred to as the "initial single-orbit sequence") corresponding to each orbit number in the "initial orbit sequence", sequential processing is performed to screen out the data whose geocentric latitude is within the latitude band of the geographical area. Specifically, in the "initial single-orbit sequence" corresponding to each orbit number, it is sequentially determined whether the geocentric latitude corresponding to each moment is greater than the lower latitude limit and less than the upper latitude limit, and satisfies the pre-specified ascending / descending orbit imaging flag. When the judgment is yes, it passes the screening, otherwise it is eliminated. Each "initial single-orbit sequence" that has completed the screening is called the "intermediate single-orbit sequence" corresponding to that orbit.

[0086] The upper latitude limit and the lower latitude limit are respectively the maximum and minimum latitudes of the geographical area. The calculation formula for the geocentric latitude is as follows:

[0087]

[0088] In the formula, φ is the geocentric latitude; P z is the Z component of the position vector data in the initial single-orbit sequence; a is the semi-major axis of the orbit.

[0089] If the ascending / descending orbit imaging flag is specified as "ascending orbit imaging", when the Z component of the satellite velocity is greater than 0, it is recorded as meeting the ascending / descending orbit imaging flag; otherwise, it does not meet the requirement. If it is set to "descending orbit imaging", when the Z component of the satellite velocity is less than 0, it is recorded as meeting the ascending / descending orbit imaging flag; otherwise, it does not meet the requirement.

[0090] Step 4.2: Convert the position of each point in the geographical boundary point set to the satellite's orbital coordinate system one by one to obtain the converted geographical boundary point set corresponding to each intermediate single-orbit sequence, and extract the minimum extreme point and the maximum extreme point from the converted geographical boundary point set in the specified azimuth.

[0091] Process the "intermediate single-orbit sequences" corresponding to each orbit number in sequence. For the data of each orbit, for the data at a single moment, convert the position of each point in the geographical area boundary point set to the satellite's orbital coordinate system (hereinafter referred to as the "orbital system") one by one. The conversion relationship is expressed by the following formula:

[0092]

[0093] In the formula, is the coordinate of a point in the orbital system of the position of a point in the geographical area boundary point set, is its corresponding geocentric coordinate system coordinate, and L oi is the coordinate transformation matrix from the inertial system to the orbital system.

[0094] Finally, select the westernmost point (i.e., the minimum extreme point) in the set and record it as Select the easternmost point (i.e., the maximum extreme point) in the set and record it as as the above extreme points; select the minimum value in and record it as {|S|} min ; select the maximum value in the set and record it as {|S|} max .

[0095] Step 4.3: Eliminate the orbital sequences that are necessarily unable to photograph the independent geographical area based on the preset screening conditions to obtain the transit orbital sequences.

[0096] In a specific implementation manner, for the "intermediate single-orbit sequences" of each orbit, screening is performed in sequence. The specific criterion is that if any of the following criteria are met, it is eliminated, that is, it is considered that this orbit is not a transit orbit segment: (1) The Z component of the position of the first point in the geographical boundary point set is greater than the radius of the earth, that is, when the z component of the position of the first point in the set of this orbit is greater than the radius of the earth; (2) The minimum extreme point is greater than the maximum value of the central ground distance of each wave position of the payload, that is, (3) The maximum extreme point is less than the minimum of the center distances of each wave position of the load, that is For those not excluded, the "intermediate orbit sequence" of this orbit is determined as the "target orbit sequence", hereinafter referred to as the "transit orbit sequence".

[0097] Step Five: Coordinate conversion section: All calculations and logical judgments involved in the evaluation of the imaging feasibility of each wave position are carried out in the satellite coordinate system.

[0098] In Step Five, the geographical area boundary points are converted from the geodetic coordinate system to the satellite coordinate system and compared and judged in the satellite coordinate system.

[0099] In each orbit, the orbital data is encrypted by time. For all independent area boundary point data, each boundary point is processed in turn, and the position coordinates of each boundary point of each independent geographical area are converted to the satellite coordinate system. Based on the encrypted orbital data and the position coordinates of the boundary points in the satellite coordinate system, the boundary point data in the satellite coordinate system corresponding to each transit orbit sequence is obtained, hereinafter referred to as the transit map, such as Figure 4 A schematic diagram of a transit map as shown.

[0100] In specific implementation, the target orbit sequence is encrypted by time, and the time interval is set to a small value, such as 0.1 second.

[0101] In specific implementation, the "satellite coordinate system" is: a two-dimensional coordinate system with the origin in the horizontal plane of the satellite. The +Y axis points forward along the velocity direction of the satellite's geodetic coordinate system, and the +X axis points to the right perpendicular to the velocity direction of the geodetic coordinate system.

[0102] In specific implementation, the position coordinates of each boundary point of each independent geographical area are converted to the satellite coordinate system, and this embodiment of the present invention will not continue to elaborate on this. The horizontal and vertical coordinates of the calculation results of each point are respectively denoted as R km , u km . u km The establishment principle of u is: the point with the minimum Y-direction component satisfies u km = 0, which is used to define the origin position of the ordinate.

[0103] Step Six: Imaging array division section: The operation plan is divided into blocks in the form of a grid. Among them, the longitudinal direction is a discrete division, and the horizontal direction is a continuous interval. The grid coordinates of the divided operation plan and the wave position imaging range coordinates of the satellite are translated to a unified coordinate system.

[0104] Specifically, the following steps 6.1 to 6.3 can be referred to:

[0105] Step 6.1, According to the azimuth dimension in the load wave position size and the load coverage overlap rate, determine the number of rows of the imaging array based on the distance scale in the longitudinal direction of all transit maps.

[0106] In an embodiment of the present invention, considering the set of transit maps corresponding to all transit orbit sequences comprehensively, the maximum number of imaging times required in the longitudinal direction is obtained according to the distance scale in the longitudinal direction thereof, and it is defined as the number of rows of the imaging array. Specifically, the number of rows of the imaging array is determined according to the distance scale in the longitudinal direction, which is denoted as follows:

[0107]

[0108] In the formula, maxY is the maximum value of the set of boundary points of all transit maps in the Y direction, is the ceiling function.

[0109] Step 6.2, in the transit map corresponding to each transit orbit sequence, based on the number of rows of the imaging array, the row imaging array is determined according to the distance scale of the transit map in the transverse direction.

[0110] In an embodiment of the present invention, in the transit map corresponding to each valid orbit sequence, for each row of the imaging array, according to the distance scale of the corresponding transit map in the transverse direction, the imaging array corresponding to this row is generated. Figures 5 to 11 A simulation of the imaging array for 6 transits is given, and the visible ranges are respectively shown in the figure. Among them, Figure 5 is a schematic diagram of the imaging array division for the first valid transit, Figure 6 is a schematic diagram of the imaging array division for the second valid transit, Figure 7 is a schematic diagram of the imaging array division for the third valid transit, Figure 8 is a schematic diagram of the imaging array division for the fourth valid transit, Figure 9 is a schematic diagram of the imaging array division for the fifth valid transit, Figure 10 is a schematic diagram of the imaging array division for the sixth valid transit, Figure 11 is a schematic diagram of the imaging array division for the seventh valid transit.

[0111] Specifically, for the transit map of the c-th transit, the set of row intervals of the imaging array is determined according to the distance scale in the transverse direction, which is denoted as follows:

[0112]

[0113] In the formula, [a, b] represents the interval from a to b, respectively represent the subset corresponding to the i-th row of the imaging array in the d-th independent geographical region, that is, the Y component u of the position in the set of boundary points of this independent geographical region km The subset included within the upper and lower limits of the i-th row of the imaging array is represented as follows:

[0114]

[0115] where maxY c is the maximum value of the Y component of the position of the set of boundary points in the transit map for the c-th transit. Take the union of all corresponding d to obtain the imaging array for this row corresponding to all independent geographical regions, denoted as Y i is the ordinate u of the boundary points within the i-th row imaging array km .

[0116] Step 6.3, after translating the row imaging array left and right, take the union of the row imaging arrays corresponding to the same row in all transit maps to obtain the imaging array for each satellite transit.

[0117] In the embodiment of the present invention, the imaging arrays corresponding to the transit maps of each time are successively translated left and right to a unified coordinate system. For each row, take the union of the array intervals corresponding to that row in all transit maps. Form an imaging array division schematic diagram as shown in Figure 12 . Specifically, for the corresponding to each transit (i = 1, 2,..., RowNum), perform a translation of the Y coordinate axis, and the amount of translation to the left is denoted as satisfying: the centroid of the set of boundary points of the transit map for this time (see the mathematical definition of "centroid") is exactly on the Y axis. Thus, there is For each row of data, take the union of all corresponding to the transit serial numbers c to obtain When contains more than 1 discontinuous interval, denote it as to represent the j-th interval.

[0118] Step Seven, imaging strategy formulation step, Step Eight, imaging array update step: formulate and update the imaging strategy in the form of a double loop, where the outer loop of the double loop is the number of regression periods, and the inner loop is the transit serial number.

[0119] For the first transit serial number of the first regression period, the imaging array is the entire imaging array; otherwise, the imaging array is the remaining imaging array after update (Step Eight). Evaluate all combinations of wave position numbers and imaging array row numbers to determine whether they are "imageable". Generate the imaging strategy for this transit based on the evaluation results. If there is no "imageable" combination, skip this inner loop and return to the beginning of Step Seven to execute the next inner loop.

[0120] In the outer loop, for each transit serial number within the current regression period, the evaluation of whether imaging is possible is performed in sequence, and the current imaging array is updated to obtain a new current imaging array; continue to perform the evaluation of whether imaging is possible for each transit serial number within the next regression period in sequence, and update the current imaging array to obtain a new current imaging array. When the imaging array is completely covered, the cumulative number of times of the outer loop is used as the target regression period number of the satellite.

[0121] In the inner loop, the combinations of all wave position numbers and imaging array row numbers are evaluated to determine whether they are "imaginable", and then an imaging strategy for the current transit is generated based on the evaluation results; at the same time, in the inner loop, the complement and union calculations are performed based on the non-imaged imaging array interval and the imaging interval generated by the selected imaging strategy, and the remaining non-imaged imaging array is calculated and updated. The embodiment of the present invention provides a specific implementation manner of the inner loop, including:

[0122] (a) For the current transit serial number within the current regression period, for the imaging array corresponding to any combination of a wave position number and an imaging array row number in the current imaging array, if it is determined that the imaging array corresponding to this combination is imaginable according to the range dimension in the payload wave position size, then this combination is used as an alternative imaging strategy corresponding to the current transit serial number, and a target imaging strategy corresponding to the current transit serial number is randomly determined from the alternative imaging strategies corresponding to the current transit serial number.

[0123] Regarding the evaluation of "imaginable", specifically, during the processing of the transit serial number c, for the wave position number n and the imaging array row number i, all j are sequentially determined. When there is one satisfying the following criterion, it is determined that this wave position / row number combination is "imaginable" during the current transit; otherwise, it is "not imaginable".

[0124] and

[0125] Randomly select a group from the set of wave position / row number combinations that satisfy imaginable as the target imaging strategy for the current transit corresponding to the transit serial number c.

[0126] (b) Update the imaging array based on the target imaging strategy to obtain a new current imaging array.

[0127] Update the current imaging array according to the following formula:

[0128]

[0129] where is the new current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy; The current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy, where A and B are intermediate parameters, and S nsel is the central ground distance of the selected wave position number nsel in the target imaging strategy, and H R is the range dimension in the payload wave position size.

[0130] (c) Continue to determine the target imaging strategy corresponding to the next transit serial number within the current regression cycle until the target imaging strategy corresponding to each transit serial number within the current regression cycle is determined, and then update the current imaging array again according to the target imaging strategy corresponding to the last transit serial number within the current regression cycle to obtain a new current imaging array.

[0131] After the target imaging strategy for each transit serial number within the current regression cycle has been determined, the first transit serial number (i.e., the next outer loop) of the next regression cycle number can be started. Repeat this process until all imaging arrays are completed, such as Figure 13 shown in an instantaneous state display of a cyclic process.

[0132] Step Nine: Result Statistics Link: Record the cumulative number of times of the outer loop experienced as the regression cycle number, and use the following formula to calculate the number of days required to complete full coverage imaging of the specified geographical area: Full Coverage Days = Regression Cycle Number × Regression Days.

[0133] It should be noted that the embodiments of the present invention are based on the description of the SAR satellite spotlight mode, and should also include other modes with a single imaging range being rectangular or satellites of other payload types. The embodiments of the present invention are also an evaluation and verification platform for an imaging strategy, and the optimization and improvement of the imaging strategy do not deviate from the structural framework of the embodiments of the present invention.

[0134] In summary, the embodiments of the present invention are based on the spotlight imaging mode of a synthetic aperture radar (SAR) satellite. In the sense of a regression orbit, a complete simulation solution for the number of days required to generate a complete image is systematically proposed. The embodiments of the present invention can be run with one key, and can stably output results under different payload parameters, satellite orbits, and target areas, effectively improving the accuracy of the calculation results and meeting the more refined analysis requirements in actual work.

[0135] Based on the foregoing embodiments, the embodiments of the present invention provide a numerical simulation evaluation device for satellite imaging coverage ability. Refer to Figure 14 the structural schematic diagram of a numerical simulation evaluation device for satellite imaging coverage ability shown, and the device mainly includes the following parts:

[0136] A data acquisition module 1402, configured to acquire payload wave position configuration parameters of a satellite and a set of geographical boundary points of multiple independent geographical regions, where the payload wave position configuration parameters include the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate;

[0137] A transit orbit sequence determination module 1404, configured to perform orbit recursion based on the epoch orbit elements of the satellite according to a prediction duration and a specified time interval to generate an initial orbit sequence of the satellite, and perform visibility screening on the initial orbit sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminate the orbit sequences that are necessarily unable to photograph the independent geographical regions to obtain a transit orbit sequence;

[0138] An imaging array division module 1406, configured to obtain a transit map corresponding to each transit orbit sequence by performing coordinate system conversion on the set of geographical boundary points, and perform operation partitioning in the form of grid division in the transit map corresponding to each transit orbit sequence according to the payload wave position size and the payload coverage overlap rate to obtain an imaging array for each transit of the satellite;

[0139] A loop evaluation module 1408, configured to perform a loop evaluation on whether the imaging array for each transit of the satellite can be imaged with the number of regression cycles as the outer loop and the transit serial number as the inner loop, and until the imaging array is completely covered, determine the target regression cycle number of the satellite based on the cumulative number of times of the outer loop.

[0140] The numerical simulation evaluation device for the satellite imaging coverage ability provided by the embodiment of the present invention, through simulation, simulates the transit scenario of the satellite, divides an imaging array for a given geographical region, and based on the imaging strategy during each effective transit, completes the corresponding part of the imaging array until the imaging history covers the entire region, and outputs the target regression cycle number required for full-coverage imaging. The embodiment of the present invention is a good alternative to the simple estimation method for the satellite imaging coverage ability, makes up for the shortcoming that the result credibility of the simple evaluation method is uncertain, and provides an important reference basis with practical value for satellite demonstration and business negotiation; on the other hand, the embodiment of the present invention is also an evaluation architecture for a set of satellite imaging strategies, provides a quantitative analysis means for the execution efficiency of the imaging strategy, and is an important cornerstone for the design and optimization of the imaging strategy.

[0141] In one implementation manner, the transit orbit sequence determination module 1404 is specifically configured to:

[0142] According to the set of geographical boundary points and the imaging flags carried in the initial single-orbit sequence corresponding to each orbit number in the initial orbit sequence, screen the intermediate single-orbit sequences, where the imaging flags include an ascending orbit imaging flag or a descending orbit imaging flag;

[0143] Convert the position of each point in the set of geographical boundary points one by one to the orbital coordinate system of the satellite to obtain the set of converted geographical boundary points corresponding to each intermediate single-track sequence, and extract the minimum extreme point and the maximum extreme point from the set of converted geographical boundary points in a specified orientation;

[0144] Based on preset screening conditions, eliminate the orbital sequences that are necessarily unable to photograph independent geographical regions to obtain the transit orbital sequences. The preset screening conditions include: the Z component of the position of the first point in the set of geographical boundary points is greater than the radius of the earth, and the minimum extreme point is greater than the maximum value of the central ground distances of each wave position of the payload, and the maximum extreme point is less than the minimum value of the central ground distances of each wave position of the payload.

[0145] In one implementation, the imaging array division module 1406 is specifically configured to:

[0146] Determine the number of rows of the imaging array according to the azimuth dimension in the payload wave position size and the payload coverage overlap rate, based on the distance scale in the longitudinal direction of all transit maps;

[0147] In each transit map corresponding to each transit orbital sequence, based on the number of rows of the imaging array, determine the row imaging array according to the distance scale in the transverse direction of the transit map;

[0148] After translating the row imaging array left and right, take the union of the row imaging arrays corresponding to the same row of all transit maps to obtain the imaging array for each satellite transit.

[0149] In one implementation, the imaging array is a plurality of imaging intervals that are longitudinally discrete and transversely continuous.

[0150] In one implementation, the loop evaluation module 1408 is specifically configured to:

[0151] For each transit serial number in the current regression period, sequentially evaluate whether imaging is possible, and update the current imaging array to obtain a new current imaging array;

[0152] Continue to sequentially evaluate whether imaging is possible for each transit serial number in the next regression period, and update the current imaging array to obtain a new current imaging array. When the imaging array is completely covered, use the cumulative number of times of the outer loop as the target regression period number of the satellite.

[0153] In one implementation, the loop evaluation module 1408 is specifically configured to:

[0154] For the current transit serial number within the current regression period, for the imaging array corresponding to any combination of a wave position number and an imaging array row number in the current imaging array, if it is determined that the imaging array corresponding to this combination can be imaged according to the range dimension in the payload wave position size, then this combination is used as an alternative imaging strategy corresponding to the current transit serial number, and a target imaging strategy corresponding to the current transit serial number is randomly determined from the alternative imaging strategies corresponding to the current transit serial number;

[0155] Update the imaging array based on the target imaging strategy to obtain a new current imaging array;

[0156] Continue to determine the target imaging strategy corresponding to the next transit serial number within the current regression period until the target imaging strategy corresponding to each transit serial number within the current regression period is determined, and then update the current imaging array again according to the target imaging strategy corresponding to the last transit serial number within the current regression period to obtain a new current imaging array.

[0157] In one implementation manner, the loop evaluation module 1408 is specifically configured to:

[0158] Update the current imaging array according to the following formula:

[0159]

[0160] where is the new current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy; is the current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy, A and B are intermediate parameters, S nsel is the central ground distance of the selected wave position number nsel in the target imaging strategy, H R is the range dimension in the payload wave position size.

[0161] The device provided by the embodiments of the present invention has the same implementation principle and the same technical effects as those of the foregoing method embodiments. For the sake of brief description, for the parts not mentioned in the device embodiments, reference may be made to the corresponding content in the foregoing method embodiments.

[0162] The embodiments of the present invention provide an electronic device. Specifically, the electronic device includes a processor and a storage device; a computer program is stored on the storage device, and when the computer program is run by the processor, it executes the method according to any one of the above-mentioned implementation manners.

[0163] Figure 15A schematic structural diagram of an electronic device provided by an embodiment of the present invention. The electronic device 100 includes: a processor 150, a memory 151, a bus 152, and a communication interface 153. The processor 150, the communication interface 153, and the memory 151 are connected through the bus 152. The processor 150 is configured to execute an executable module stored in the memory 151, such as a computer program.

[0164] Among them, the memory 151 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk memory. Through at least one communication interface 153 (which can be wired or wireless), a communication connection is established between this system network element and at least one other network element. The Internet, a wide area network, a local area network, a metropolitan area network, etc. can be used.

[0165] The bus 152 can be an ISA bus, a PCI bus, an EISA bus, etc. The bus can be divided into an address bus, a data bus, a control bus, etc. For the sake of simplicity of representation, Figure 15 only a bidirectional arrow is used in the figure, but it does not mean that there is only one bus or one type of bus.

[0166] Among them, the memory 151 is used to store a program. After receiving an execution instruction, the processor 150 executes the program. The method executed by the device defined by the flow process disclosed in any one of the foregoing embodiments of the present invention can be applied to the processor 150 or implemented by the processor 150.

[0167] The processor 150 may be an integrated circuit chip with the ability to process signals. In the implementation process, each step of the above method can be completed by the integrated logic circuit of the hardware in the processor 150 or the instructions in the form of software. The above-mentioned processor 150 may be a general-purpose processor, including a central processing unit (CPU for short), a network processor (NP for short), etc.; it may also be a digital signal processor (DSP for short), an application specific integrated circuit (ASIC for short), a field-programmable gate array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps and logic block diagrams disclosed in the embodiments of the present invention. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present invention can be directly embodied as being executed and completed by the hardware decoding processor, or executed and completed by the combination of the hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory 151, and the processor 150 reads the information in the memory 151 and combines its hardware to complete the steps of the above method.

[0168] The computer program product of the readable storage medium provided by the embodiments of the present invention includes a computer-readable storage medium storing program code, and the instructions included in the program code can be used to execute the methods described in the foregoing method embodiments. For the specific implementation, reference can be made to the foregoing method embodiments, which will not be elaborated here.

[0169] If the above-mentioned functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The foregoing storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs that can store program codes.

[0170] Finally, it should be noted that the above-mentioned embodiments are only specific embodiments of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: any person skilled in the art within the technical scope disclosed by the present invention can still modify the technical solutions described in the foregoing embodiments or can easily conceive of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes, or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention and should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A numerical simulation evaluation method for satellite imaging coverage ability, characterized in that Including: Obtaining the payload wave position configuration parameters of the satellite, and obtaining the set of geographical boundary points of multiple independent geographical regions, where the payload wave position configuration parameters include the central ground distance of each wave position of the payload, the payload wave position size, and the payload coverage overlap rate; Based on the epoch orbital elements of the satellite, performing orbital recursion according to the forecast duration and the specified time interval to generate the initial orbital sequence of the satellite, and performing visibility screening on the initial orbital sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminating the orbital sequences that are necessarily unable to photograph the independent geographical region to obtain the transit orbital sequence; Performing coordinate system conversion on the set of geographical boundary points to obtain the transit map corresponding to each transit orbital sequence, and performing operation block division in the form of grid division in each transit map corresponding to each transit orbital sequence according to the payload wave position size and the payload coverage overlap rate to obtain the imaging array for each transit of the satellite; Taking the number of regression cycles as the outer loop and the transit serial number as the inner loop, performing a loop evaluation on whether the imaging array for each transit of the satellite can be imaged until the imaging array is completely covered, and determining the target regression cycle number of the satellite based on the cumulative number of times of the outer loop.

2. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 1, characterized in that Performing visibility screening on the initial orbital sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminating the orbital sequences that are necessarily unable to photograph the independent geographical region to obtain the transit orbital sequence, including: Screening the intermediate single-rail sequences according to the set of geographical boundary points and the imaging flags carried by the initial single-rail sequences corresponding to each orbital number in the initial orbital sequence, where the imaging flags include ascending orbit imaging flags or descending orbit imaging flags; Converting the position of each point in the set of geographical boundary points to the orbital coordinate system of the satellite one by one to obtain the set of transformed geographical boundary points corresponding to each intermediate single-rail sequence, and extracting the minimum extreme point and the maximum extreme point from the set of transformed geographical boundary points in the specified azimuth; Eliminating the orbital sequences that are necessarily unable to photograph the independent geographical region based on the preset screening conditions to obtain the transit orbital sequence, where the preset screening conditions include: the Z component of the position of the first point in the set of geographical boundary points is greater than the radius of the earth, and the minimum extreme point is greater than the maximum value of the central ground distance of each wave position of the payload, and the maximum extreme point is less than the minimum value of the central ground distance of each wave position of the payload.

3. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 1, characterized in that Performing operation block division in the form of grid division in each transit map corresponding to each transit orbital sequence according to the payload wave position size and the payload coverage overlap rate to obtain the imaging array for each transit of the satellite, including: Determining the number of rows of the imaging array according to the azimuth dimension in the payload wave position size and the payload coverage overlap rate, and the longitudinal distance scale of all the transit maps; In each transit map corresponding to each transit orbital sequence, determining the row imaging array based on the number of rows of the imaging array and the transverse distance scale of the transit map. After the line imaging array is translated left and right, the union of the line imaging arrays corresponding to the same line of all the transit maps is obtained to get the imaging array for each satellite transit.

4. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 3, characterized in that The imaging array is a plurality of imaging intervals that are longitudinally discrete and laterally continuous.

5. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 1, characterized in that, Taking the number of regression cycles as the outer loop and the transit serial number as the inner loop, a loop evaluation of whether the imaging array for each satellite transit can be imaged is performed until the imaging array is completely covered. Based on the cumulative number of times of the outer loop, determining the target regression cycle number of the satellite includes: For each transit serial number within the current regression cycle, an evaluation of whether it can be imaged is sequentially performed, and the current imaging array is updated to obtain a new current imaging array; Continue to perform an evaluation of whether it can be imaged for each transit serial number within the next regression cycle, and update the current imaging array to obtain a new current imaging array until the imaging array is completely covered. Then, take the cumulative number of times of the outer loop as the target regression cycle number of the satellite.

6. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 5, wherein For each transit serial number within the current regression cycle, an evaluation of whether it can be imaged is sequentially performed, and the current imaging array is updated to obtain a new current imaging array, including: For the current transit serial number within the current regression cycle, for the imaging array corresponding to any combination of the wave position number and the imaging array row number in the current imaging array, if it is determined that the imaging array corresponding to this combination can be imaged according to the distance dimension in the load wave position size, then take this combination as the alternative imaging strategy corresponding to the current transit serial number, and randomly determine the target imaging strategy corresponding to the current transit serial number from the alternative imaging strategies corresponding to the current transit serial number; Update the imaging array based on the target imaging strategy to obtain a new current imaging array; Continue to determine the target imaging strategy corresponding to the next transit serial number within the current regression cycle until the target imaging strategies corresponding to each transit serial number within the current regression cycle are determined, and then update the current imaging array again according to the target imaging strategy corresponding to the last transit serial number within the current regression cycle to obtain a new current imaging array.

7. The numerical simulation evaluation method for satellite imaging coverage ability according to claim 6, wherein Updating the current imaging array based on the target imaging strategy to obtain a new current imaging array includes: Updating the current imaging array according to the following formula: Among them, is the new current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy; is the current imaging array corresponding to the selected imaging array row number nsel in the target imaging strategy, A and B are intermediate parameters, S nsel is the central ground distance of the selected wave position number nsel in the target imaging strategy, H R is the range dimension in the payload wave position size.

8. A numerical simulation evaluation device for satellite imaging coverage ability, characterized in that, Including: A data acquisition module, configured to acquire the load wave position configuration parameters of the satellite and acquire the set of geographical boundary points of multiple independent geographical regions. The load wave position configuration parameters include the central ground distance of each load wave position, the load wave position size, and the load coverage overlap rate; The transit orbit sequence determination module is configured to perform orbit recursion based on the epoch orbit elements of the satellite according to the prediction duration and the specified time interval, generate the initial orbit sequence of the satellite, and perform visibility screening on the initial orbit sequence according to the central ground distance of each wave position of the payload and the set of geographical boundary points, and eliminate the orbit sequences that are necessarily unable to photograph the independent geographical area to obtain the transit orbit sequence; The imaging array division module is configured to obtain the transit map corresponding to each transit orbit sequence by performing coordinate system conversion on the set of geographical boundary points, and perform operation block division in the form of grid division in the transit map corresponding to each transit orbit sequence according to the wave position size of the payload and the payload coverage overlap rate, to obtain the imaging array for each transit of the satellite; The loop evaluation module is configured to perform loop evaluation on whether the imaging array for each transit of the satellite can be imaged, with the number of regression periods as the outer loop and the transit serial number as the inner loop, until the imaging array is completely covered, and determine the target regression period number of the satellite based on the cumulative number of times of the outer loop.

9. An electronic device, characterized in that, It includes a processor and a memory. The memory stores computer executable instructions that can be executed by the processor. The processor executes the computer executable instructions to implement the method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer executable instructions. When the computer executable instructions are called and executed by the processor, the computer executable instructions cause the processor to implement the method according to any one of claims 1 to 7.

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