Method, device and storage medium for obtaining multi-layer satellite constellation parameters

Abstract

The present application provides a method, device, and storage medium for obtaining multi-layer satellite constellation parameters. The method includes: determining multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of satellite constellation in the multi-layer satellite constellation to obtain the corresponding average visible satellite ratio of ground nodes; obtaining satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters, and determining multiple multi-layer satellite parameters based on the satellite configuration parameters and basic communication parameters; obtaining the ground coverage capacity of the multi-layer satellite constellation based on the multi-layer satellite parameters, satellite configuration parameters, and the average visible satellite ratio of ground nodes of each layer of satellite constellation, and determining the corresponding Spearman correlation coefficient in combination with the ground communication requirements; and iteratively updating the constellation parameters of the multi-layer satellite constellation based on the target optimization algorithm and the Spearman correlation coefficient to obtain the optimal multi-layer satellite constellation parameters, thereby achieving the technical effect of improving the efficiency of obtaining multi-layer satellite constellation parameters.

Description

Technical Field

[0001] The present application relates to the field of data processing, and in particular to a method, device, and storage medium for obtaining multi-layer satellite constellation parameters. Background Art

[0002] With the development of wireless communication technology, the number of various mobile terminals has increased rapidly, the scale of the Internet of Things has become increasingly large, and the trend of the Internet of Everything is emerging. In this context, the low-orbit satellite network, as a communication system that can provide global wide-area coverage, has become an important supplement to the terrestrial communication network. Together with high-altitude platforms, drones, ground base stations and other facilities, it constitutes a space-ground integrated network. In order to make the performance of the low-orbit satellite constellation meet the needs of the space-ground integrated network, it is necessary to carry out detailed design of the multi-layer satellite constellation parameters. Therefore, the acquisition of multi-layer satellite constellation parameters has become a direction with application prospects.

[0003] In the existing technology, the method for obtaining multi-layer satellite constellation parameters mainly estimates the multi-layer satellite constellation parameters through random geometry methods and algorithm flow estimation methods, assuming that satellites are evenly distributed on the satellite spherical shell and the positions of each satellite are independent of each other.

[0004] Since the random geometry method and algorithm flow estimation method in the existing technology are highly complex, the overall estimation process is time-consuming. At the same time, the use of the random geometry method ignores the position coupling relationship between low-orbit satellites, which is inconsistent with the fact that satellites in the actual low-orbit constellation network are distributed according to orbit and have position correlation. The obtained multi-layer satellite constellation parameters have low reliability and insufficient credibility. At the same time, the uneven distribution of ground communication needs is ignored, resulting in poor accuracy of the multi-layer satellite constellation parameters and the technical problem of low efficiency in obtaining the multi-layer satellite constellation parameters. Summary of the Invention

[0005] The present application provides a method, device, and storage medium for obtaining multi-layer satellite constellation parameters, so as to achieve the technical effect of improving the efficiency of obtaining multi-layer satellite constellation parameters.

[0006] In a first aspect, the present application provides a method for obtaining multi-layer satellite constellation parameters, comprising:

[0007] Determine multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation to obtain the average visible satellite ratio of the corresponding ground nodes, wherein the single-layer satellite parameters include the longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation;

[0008] Obtaining the satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters, and determining multiple multi-layer satellite parameters based on the satellite configuration parameters and basic communication parameters. The multi-layer satellite parameters include the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, and the minimum proportion of satellites in each layer;

[0009] The ground coverage capacity of a multi-layer satellite constellation is obtained based on multi-layer satellite parameters, satellite configuration parameters, and the average visible satellite ratio of ground nodes in each layer of satellite constellation. The corresponding Spearman correlation coefficient is determined in combination with ground communication requirements.

[0010] According to the target optimization algorithm and the Spearman correlation coefficient, the constellation parameters of the multi-layer satellite constellation are iteratively updated to obtain the optimal multi-layer satellite constellation parameters, wherein the target optimization algorithm includes the sparrow algorithm and the chaos mapping algorithm.

[0011] Optionally, the orbital parameters include satellite orbit altitude, orbital inclination, number of orbital planes, and number of satellites in each orbital plane; the ground node parameters include latitude parameters and elevation parameters of the ground nodes; and multiple single-layer satellite parameters are determined based on the orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation, including:

[0012] According to the elevation angle parameters of the ground node and the satellite orbit height, the geocentric angle corresponding to the visible range of the ground node to the satellite is determined;

[0013] According to the geocentric angle, orbital inclination and latitude parameters of the ground node, multiple position phases corresponding to the visible satellite cap are obtained respectively, where the position phases include the north phase, the south phase and the middle phase;

[0014] Determine the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point based on the positional relationship between the position phase and the orbital inclination, and determine the longitude range corresponding to the satellite phase median point based on the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point;

[0015] According to the number of orbital planes, the corresponding satellite density is obtained, and according to the longitude range and satellite density corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation is determined;

[0016] The number of visible satellites in a single-layer satellite constellation is determined based on the latitude parameters of the ground node, the phase numbers of the upper and lower parts of the satellite sphere visible from the ground node, and the time average of the number of visible satellites in the single-layer satellite constellation.

[0017] Optionally, determining the target phase numbers of the upper and lower parts of the satellite cap visible from the ground node and the target latitude corresponding to the phase median point based on the positional relationship between the position phase and the orbital inclination includes:

[0018] If the orbital inclination is higher than the north phase, determining a first phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node according to the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one first phase difference;

[0019] Determine, based on the first phase difference and the number of satellites in each orbital plane, the first phase numbers of the upper and lower portions of the satellite spherical cap visible from the ground node, and determine, based on the orbital inclination, the north phase, the south phase, and the intermediate phase, the first latitude corresponding to the phase median point, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to a first latitude;

[0020] If the orbital inclination is lower than the north phase and higher than the middle phase, then determining a second phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one second phase difference;

[0021] Determine the second phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node based on the second phase difference and the number of satellites in each orbital plane, and determine the second latitude corresponding to the phase median point based on the orbital inclination, the north phase, the south phase, and the intermediate phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a second latitude;

[0022] If the orbital inclination is lower than the middle phase and higher than the south phase, then determine the third phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one third phase difference;

[0023] According to the third phase difference and the number of satellites in each orbital plane, the third phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node are determined, and according to the orbital inclination, north phase, south phase and intermediate phase, the third latitude corresponding to the phase median point is determined, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a third latitude.

[0024] Optionally, obtain the average visible satellite ratio of the corresponding ground node, including:

[0025] The longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in a single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are input into a first target model to obtain an average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation output by the first target model. The first target model is a mathematical model for calculating the average ratio of visible satellites for ground nodes corresponding to each single-layer satellite constellation in a multi-layer satellite constellation. The average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation is achieved by the following method:

[0026]

[0027] in, Represents the average visible satellite ratio of ground nodes corresponding to a single-layer satellite constellation, represents the number of visible satellites in a single-layer satellite constellation, M represents the number of orbital planes, N represents the number of satellites in each orbital plane, α represents the orbital inclination, and h represents the satellite orbit height. represents the latitude parameter of the ground node, i represents the upper and lower parts of the satellite cap visible from the ground node, ΔPhase i Represents the phase difference between the upper and lower parts of the satellite cap visible to the ground node, λ i represents the target latitude corresponding to the phase median point, and β represents the elevation angle parameter of the ground node.

[0028] Optionally, the satellite configuration parameters include the total number of satellites in all layers, the satellite orbit altitude range, and the orbit inclination range; the basic communication parameters include the receiving power, bandwidth, noise power spectrum density, transmitting and receiving antenna gains, and satellite wavelength between the ground node and the satellite; and multiple layers of satellite parameters are determined based on the satellite configuration parameters and the basic communication parameters, including:

[0029] Determine the path loss between the ground node and the satellite based on the satellite wavelength and the altitude range of the satellite orbit;

[0030] Determine the accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation based on path loss, received power between ground nodes and satellites, bandwidth, noise power spectral density, and transmitter and receiver antenna gains;

[0031] Get the minimum number of orbital planes and the minimum number of satellites in each orbital plane for each layer in a multi-layer satellite constellation. Based on the minimum number of orbital planes, the minimum number of satellites in each orbital plane, and the total number of satellites in all layers, get the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation. The maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation are obtained in the following way:

[0032] S max =floor(SatNum / M min / N min)

[0033] ρ min =M min ·N min / SatNum

[0034] Among them, S max Represents the maximum number of satellite layers corresponding to a multi-layer satellite constellation, floor represents the floor rounding function, ρ min Represents the minimum proportion of satellites in each layer, SatNum represents the total number of satellites in all layers, M min Represents the minimum number of orbital surfaces, N min Represents the minimum number of satellites per orbital plane.

[0035] Optionally, obtaining the ground coverage capacity of the multi-layer satellite constellation according to the multi-layer satellite parameters, the satellite configuration parameters, and the average visible satellite ratio of the ground nodes of each layer of the satellite constellation includes:

[0036] The accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of ground nodes are input into a second target model to obtain the ground coverage capacity corresponding to the multi-layer constellation output by the second target model. The second target model is a mathematical model for calculating the ground coverage capacity of the multi-layer satellite constellation. The ground coverage capacity corresponding to the multi-layer satellite constellation is achieved by the following method:

[0037]

[0038] in, represents the ground coverage capacity corresponding to the multi-layer constellation, S represents the maximum number of satellite layers in the multi-layer satellite constellation, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, M s Represents the number of orbital planes of the S-layer satellite constellation, N s represents the number of satellites in each orbital plane in the S-layer satellite constellation, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity, SatNum represents the total number of satellites in all layers, ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0039] Optionally, a corresponding Spearman correlation coefficient is determined based on the ground coverage capacity and the ground communication requirement, and is obtained in the following manner:

[0040]

[0041] in, represents the Spearman correlation coefficient, Represents the ground coverage capacity corresponding to the multi-layer constellation, represents the distribution of ground communication demand, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity is ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0042] Optionally, constellation parameters of the multi-layer satellite constellation are iteratively updated according to the target optimization algorithm and the Spearman correlation coefficient to obtain optimal multi-layer satellite constellation parameters, including:

[0043] Acquire multiple multi-layer satellite constellations that meet constellation configuration parameter requirements and constellation parameters of each layer of satellites in each multi-layer satellite constellation, and construct multiple multi-layer satellite constellation parameter matrices based on the constellation parameters of each layer of satellites in each multi-layer satellite constellation, wherein the constellation parameters include satellite altitude, satellite inclination, and satellite ratio of each layer of satellite constellation in each multi-layer satellite constellation, and one multi-layer satellite constellation corresponds to one multi-layer satellite constellation parameter matrix;

[0044] According to the sparrow algorithm, multiple multi-layer satellite constellations are aggregated as a sparrow population, and each multi-layer satellite constellation parameter matrix is ​​used as the position matrix of each sparrow in the sparrow population;

[0045] According to the chaotic mapping algorithm, an initialized sparrow population is obtained, and the position matrix of each sparrow in the initialized sparrow population is iteratively updated multiple times. After each iterative update, the Spearman correlation coefficient corresponding to each sparrow in the sparrow population is obtained, wherein one sparrow corresponds to one Spearman correlation coefficient;

[0046] After determining that the number of iterations reaches the target threshold, the maximum Spearman correlation coefficient in the sparrow population is obtained for the current number of iterations, and based on the maximum Spearman correlation coefficient, the position matrix of the sparrow corresponding to the maximum Spearman correlation coefficient is used as the optimal multi-layer satellite constellation parameter.

[0047] In a second aspect, the present application provides a device for obtaining multi-layer satellite constellation parameters, comprising:

[0048] A first processing module is configured to determine a plurality of single-layer satellite parameters based on orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation, so as to obtain an average visible satellite ratio of the corresponding ground nodes, wherein the single-layer satellite parameters include a longitude range corresponding to a satellite phase median point, a time average of the number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation;

[0049] The second processing module is used to obtain the satellite configuration parameters to be optimized, the ground communication requirements and the basic communication parameters, and determine multiple multi-layer satellite parameters based on the satellite configuration parameters and the basic communication parameters, wherein the multi-layer satellite parameters include the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, and the minimum proportion of satellites in each layer;

[0050] The third processing module is used to obtain the ground coverage capacity of the multi-layer satellite constellation based on the multi-layer satellite parameters, satellite configuration parameters and the average visible satellite ratio of the ground nodes in each layer of the satellite constellation, and determine the corresponding Spearman correlation coefficient in combination with the ground communication requirements;

[0051] The acquisition module is used to iteratively update the constellation parameters of the multi-layer satellite constellation according to the target optimization algorithm and the Spearman correlation coefficient to obtain the optimal multi-layer satellite constellation parameters, wherein the target optimization algorithm includes the sparrow algorithm and the chaos mapping algorithm.

[0052] Optionally, the first processing module is further configured to:

[0053] According to the elevation angle parameters of the ground node and the satellite orbit height, the geocentric angle corresponding to the visible range of the ground node to the satellite is determined;

[0054] According to the geocentric angle, orbital inclination and latitude parameters of the ground node, multiple position phases corresponding to the visible satellite cap are obtained respectively, where the position phases include the north phase, the south phase and the middle phase;

[0055] Determine the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point based on the positional relationship between the position phase and the orbital inclination, and determine the longitude range corresponding to the satellite phase median point based on the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point;

[0056] According to the number of orbital planes, the corresponding satellite density is obtained, and according to the longitude range and satellite density corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation is determined;

[0057] The number of visible satellites in a single-layer satellite constellation is determined based on the latitude parameters of the ground node, the phase numbers of the upper and lower parts of the satellite sphere visible from the ground node, and the time average of the number of visible satellites in the single-layer satellite constellation.

[0058] Optionally, the first processing module is further configured to:

[0059] If the orbital inclination is higher than the north phase, determining a first phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node according to the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one first phase difference;

[0060] Determine, based on the first phase difference and the number of satellites in each orbital plane, the first phase numbers of the upper and lower portions of the satellite spherical cap visible from the ground node, and determine, based on the orbital inclination, the north phase, the south phase, and the intermediate phase, the first latitude corresponding to the phase median point, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to a first latitude;

[0061] If the orbital inclination is lower than the north phase and higher than the middle phase, then determining a second phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one second phase difference;

[0062] Determine the second phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node based on the second phase difference and the number of satellites in each orbital plane, and determine the second latitude corresponding to the phase median point based on the orbital inclination, the north phase, the south phase, and the intermediate phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a second latitude;

[0063] If the orbital inclination is lower than the middle phase and higher than the south phase, then determine the third phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one third phase difference;

[0064] According to the third phase difference and the number of satellites in each orbital plane, the third phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node are determined, and according to the orbital inclination, north phase, south phase and intermediate phase, the third latitude corresponding to the phase median point is determined, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a third latitude.

[0065] Optionally, the first processing module is further configured to:

[0066] The longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in a single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are input into a first target model to obtain an average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation output by the first target model. The first target model is a mathematical model for calculating the average ratio of visible satellites for ground nodes corresponding to each single-layer satellite constellation in a multi-layer satellite constellation. The average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation is achieved by the following method:

[0067]

[0068] in, Represents the average visible satellite ratio of ground nodes corresponding to a single-layer satellite constellation, represents the number of visible satellites in a single-layer satellite constellation, M represents the number of orbital planes, N represents the number of satellites in each orbital plane, α represents the orbital inclination, and h represents the satellite orbit height. represents the latitude parameter of the ground node, i represents the upper and lower parts of the satellite cap visible from the ground node, ΔPhase i Represents the phase difference between the upper and lower parts of the satellite cap visible to the ground node, λ i represents the target latitude corresponding to the phase median point, and β represents the elevation angle parameter of the ground node.

[0069] Optionally, the second processing module is further configured to:

[0070] Determine the path loss between the ground node and the satellite based on the satellite wavelength and the altitude range of the satellite orbit;

[0071] Determine the accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation based on path loss, received power between ground nodes and satellites, bandwidth, noise power spectral density, and transmitter and receiver antenna gains;

[0072] Get the minimum number of orbital planes and the minimum number of satellites in each orbital plane for each layer in a multi-layer satellite constellation. Based on the minimum number of orbital planes, the minimum number of satellites in each orbital plane, and the total number of satellites in all layers, get the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation. The maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation are obtained in the following way:

[0073] S max =floor(SatNum / M min / N min )

[0074] ρ min =M min ·N min / SatNum

[0075] Among them, S max Represents the maximum number of satellite layers corresponding to a multi-layer satellite constellation, floor represents the floor rounding function, ρ min Represents the minimum proportion of satellites in each layer, SatNum represents the total number of satellites in all layers, M min Represents the minimum number of orbital surfaces, N min Represents the minimum number of satellites per orbital plane.

[0076] Optionally, the third processing module is further configured to:

[0077] The accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of ground nodes are input into a second target model to obtain the ground coverage capacity corresponding to the multi-layer constellation output by the second target model. The second target model is a mathematical model for calculating the ground coverage capacity of the multi-layer satellite constellation. The ground coverage capacity corresponding to the multi-layer satellite constellation is achieved by the following method:

[0078]

[0079] in, represents the ground coverage capacity corresponding to the multi-layer constellation, S represents the maximum number of satellite layers in the multi-layer satellite constellation, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, M s Represents the number of orbital planes of the S-layer satellite constellation, N s represents the number of satellites in each orbital plane in the S-layer satellite constellation, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity, SatNum represents the total number of satellites in all layers, ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0080] Optionally, the third processing module is further configured to:

[0081] According to the ground coverage capacity and ground communication requirements, the corresponding Spearman correlation coefficient is determined and obtained by the following method:

[0082]

[0083] in, represents the Spearman correlation coefficient, Represents the ground coverage capacity corresponding to the multi-layer constellation, represents the distribution of ground communication demand, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity is ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0084] Optionally, the acquisition module is further configured to:

[0085] Acquire multiple multi-layer satellite constellations that meet constellation configuration parameter requirements and constellation parameters of each layer of satellites in each multi-layer satellite constellation, and construct multiple multi-layer satellite constellation parameter matrices based on the constellation parameters of each layer of satellites in each multi-layer satellite constellation, wherein the constellation parameters include satellite altitude, satellite inclination, and satellite ratio of each layer of satellite constellation in each multi-layer satellite constellation, and one multi-layer satellite constellation corresponds to one multi-layer satellite constellation parameter matrix;

[0086] According to the sparrow algorithm, multiple multi-layer satellite constellations are aggregated as a sparrow population, and each multi-layer satellite constellation parameter matrix is ​​used as the position matrix of each sparrow in the sparrow population;

[0087] According to the chaotic mapping algorithm, an initialized sparrow population is obtained, and the position matrix of each sparrow in the initialized sparrow population is iteratively updated multiple times. After each iterative update, the Spearman correlation coefficient corresponding to each sparrow in the sparrow population is obtained, wherein one sparrow corresponds to one Spearman correlation coefficient;

[0088] After determining that the number of iterations reaches the target threshold, the maximum Spearman correlation coefficient in the sparrow population is obtained for the current number of iterations, and based on the maximum Spearman correlation coefficient, the position matrix of the sparrow corresponding to the maximum Spearman correlation coefficient is used as the optimal multi-layer satellite constellation parameter.

[0089] In a third aspect, the present application provides a device for acquiring multi-layer satellite constellation parameters, including:

[0090] processor and memory;

[0091] Memory stores computer-executable instructions;

[0092] The processor executes the computer-executable instructions stored in the memory, so that the processor executes various possible implementations of the first aspect as described above.

[0093] In a fourth aspect, the present application provides a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, they are used to implement various possible implementation methods as in the first aspect.

[0094] In a fifth aspect, the present application provides a computer program product, which, when executed by a processor, is used to implement various possible implementations as in the first aspect.

[0095] The present application provides a method, device and storage medium for obtaining multi-layer satellite constellation parameters. The method determines multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of satellite constellation in the multi-layer satellite constellation to obtain the corresponding average visible satellite ratio of ground nodes; obtains the satellite configuration parameters to be optimized, ground communication requirements and basic communication parameters, and determines multiple multi-layer satellite parameters based on the satellite configuration parameters and basic communication parameters; obtains the ground coverage capacity of the multi-layer satellite constellation based on the multi-layer satellite parameters, satellite configuration parameters and the average visible satellite ratio of ground nodes of each layer of satellite constellation, and determines the corresponding Spearman correlation coefficient in combination with the ground communication requirements; iteratively updates the constellation parameters of the multi-layer satellite constellation based on the target optimization algorithm and the Spearman correlation coefficient. , obtain the optimal multi-layer satellite constellation parameters, and thus obtain the average visible satellite ratio of the ground nodes of each layer of satellite constellation in the multi-layer satellite constellation, so that when designing the constellation, the latitude position corresponding to the highest ground coverage of the constellation can be customized to match the access needs of different regions, thereby improving the flexibility and convenience of the multi-layer satellite constellation parameter acquisition process. At the same time, the ground coverage capacity of the multi-layer satellite constellation and the corresponding Spearman correlation coefficient are obtained to obtain the optimal multi-layer satellite constellation parameters, ensuring the reliability and accuracy of the multi-layer satellite constellation parameters, reducing the complexity of the overall calculation process, saving time costs, solving the technical problem of low efficiency in obtaining multi-layer satellite constellation parameters, and achieving the technical effect of improving the efficiency of obtaining multi-layer satellite constellation parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0096] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0097] Figure 1 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 1 ;

[0098] Figure 2 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 2 ;

[0099] Figure 3A schematic diagram of the visible range of a single-layer low-orbit satellite from an Earth node provided in an embodiment of the present application;

[0100] Figure 4 A schematic diagram showing the positional relationship between the visible spherical cap and the satellite distribution range provided in an embodiment of the present application;

[0101] Figure 5 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 3 ;

[0102] Figure 6 A schematic diagram of the positions of adjacent satellites in adjacent orbits in a multi-layer satellite constellation provided in an embodiment of the present application;

[0103] Figure 7 A schematic diagram of the structure of a device for obtaining multi-layer satellite constellation parameters provided in an embodiment of the present application;

[0104] Figure 8 This is a hardware structure diagram of the device for acquiring multi-layer satellite constellation parameters provided in an embodiment of the present application.

[0105] The above drawings illustrate specific embodiments of the present application, which will be described in more detail below. These drawings and the textual description are not intended to limit the scope of the present application in any way, but rather to illustrate the concepts of the present application to those skilled in the art by reference to specific embodiments. DETAILED DESCRIPTION

[0106] Exemplary embodiments will be described in detail herein, with examples illustrated in the accompanying drawings. In the following description, when referring to the drawings, identical numerals in different figures represent identical or similar elements, unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all embodiments consistent with the present application. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present application, as detailed in the appended claims.

[0107] Since the random geometry method and algorithm flow estimation method in the existing technology are highly complex, the overall estimation process is time-consuming. At the same time, the use of the random geometry method ignores the position coupling relationship between low-orbit satellites, which is inconsistent with the fact that satellites in the actual low-orbit constellation network are distributed according to orbit and have position correlation. The obtained multi-layer satellite constellation parameters have low reliability and insufficient credibility. At the same time, the uneven distribution of ground communication needs is ignored, resulting in poor accuracy of the multi-layer satellite constellation parameters and the technical problem of low efficiency in obtaining the multi-layer satellite constellation parameters.

[0108] The present application provides a method, device, and storage medium for obtaining multi-layer satellite constellation parameters. By obtaining the average visible satellite ratio of ground nodes in each layer of the multi-layer satellite constellation, the latitude position corresponding to the constellation's highest ground coverage multiplicity can be customized and adjusted during constellation design to match the access requirements of different regions, thereby improving the flexibility and convenience of the multi-layer satellite constellation parameter acquisition process. At the same time, the ground coverage capacity of the multi-layer satellite constellation and the corresponding Spearman correlation coefficient are obtained to obtain the optimal multi-layer satellite constellation parameters, ensuring the reliability and accuracy of the multi-layer satellite constellation parameters, reducing the complexity of the overall calculation process, saving time and cost, and solving the technical problem of low efficiency in obtaining multi-layer satellite constellation parameters, thereby achieving the technical effect of improving the efficiency of obtaining multi-layer satellite constellation parameters.

[0109] The following specific embodiments describe in detail the technical solution of the present application and how the technical solution of the present application solves the above-mentioned technical problems. The following specific embodiments can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments. The embodiments of the present application will be described below in conjunction with the accompanying drawings.

[0110] Figure 1 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 1 .like Figure 1 As shown, the method for obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application includes:

[0111] S101, determining multiple single-layer satellite parameters based on orbital parameters and ground node parameters of each layer of satellite constellations in a multi-layer satellite constellation to obtain an average visible satellite ratio of corresponding ground nodes;

[0112] In this embodiment, the single-layer satellite parameters include the longitude range corresponding to the satellite phase median point, the time average number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation.

[0113] Based on the orbital parameters and ground node parameters of each layer of satellite constellation in the multi-layer satellite constellation, single-layer satellite parameters including the longitude range corresponding to the satellite phase median point, the time average number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are determined through the following S201 to S209. Based on the single-layer satellite parameters, the average visible satellite ratio of the ground nodes corresponding to each layer of satellite constellation in the multi-layer satellite constellation is obtained through the following S210.

[0114] S102: Obtain satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters, and determine multiple layers of satellite parameters based on the satellite configuration parameters and basic communication parameters;

[0115] In this embodiment, the satellite configuration parameters include the total number of satellites in all layers, the satellite orbit altitude range and the orbit inclination range. The basic communication parameters include the receiving power, bandwidth, noise power spectrum density, transmitting end and receiving end antenna gain and satellite wavelength between the ground node and the satellite. The multi-layer satellite parameters include the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation and the minimum proportion of satellites in each layer.

[0116] According to user needs, the satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters are obtained. Then, through the following S502 to S503, the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, and the minimum proportion of satellites in each layer are obtained.

[0117] S103. Obtaining the ground coverage capacity of the multi-layer satellite constellation based on multi-layer satellite parameters, satellite configuration parameters, and the average ratio of visible satellites from ground nodes in each layer of the satellite constellation, and determining the corresponding Spearman correlation coefficient in combination with ground communication requirements;

[0118] According to the multi-layer satellite parameters, satellite configuration parameters, and the average visible satellite ratio of the ground nodes of each layer of the satellite constellation, the ground coverage capacity of the multi-layer satellite constellation and the corresponding Spearman correlation coefficient are obtained through the following steps S504 to S505.

[0119] S104. Iteratively update the constellation parameters of the multi-layer satellite constellation according to the target optimization algorithm and the Spearman correlation coefficient to obtain optimal multi-layer satellite constellation parameters.

[0120] In this embodiment, the target optimization algorithm includes the sparrow algorithm and the chaos mapping algorithm.

[0121] According to the sparrow algorithm, the chaos mapping algorithm and the Spearman correlation coefficient, the optimal multi-layer satellite constellation parameters in the multi-layer satellite constellation are obtained through the following S506 to S509.

[0122] The present application provides a method for obtaining multi-layer satellite constellation parameters, which determines multiple single-layer satellite parameters according to the orbital parameters and ground node parameters of each layer of satellite constellation in the multi-layer satellite constellation to obtain the corresponding average visible satellite ratio of ground nodes; obtains the satellite configuration parameters to be optimized, ground communication requirements and basic communication parameters, and determines multiple multi-layer satellite parameters according to the satellite configuration parameters and basic communication parameters; obtains the ground coverage capacity of the multi-layer satellite constellation according to the multi-layer satellite parameters, satellite configuration parameters and the average visible satellite ratio of ground nodes of each layer of satellite constellation, and determines the corresponding Spearman correlation coefficient in combination with the ground communication requirements; iteratively updates the constellation parameters of the multi-layer satellite constellation according to the target optimization algorithm and the Spearman correlation coefficient to obtain the optimal coverage capacity. The invention obtains the optimal multi-layer satellite constellation parameters, thereby obtaining the average visible satellite ratio of the ground nodes of each layer of the multi-layer satellite constellation. When designing the constellation, the latitude position corresponding to the highest ground coverage of the constellation can be customized to match the access requirements of different regions, thereby improving the flexibility and convenience of the multi-layer satellite constellation parameter acquisition process. At the same time, the ground coverage capacity of the multi-layer satellite constellation and the corresponding Spearman correlation coefficient are obtained to obtain the optimal multi-layer satellite constellation parameters, thereby ensuring the reliability and accuracy of the multi-layer satellite constellation parameters, reducing the complexity of the overall calculation process, saving time and cost, solving the technical problem of low efficiency in acquiring the multi-layer satellite constellation parameters, and achieving the technical effect of improving the efficiency of acquiring the multi-layer satellite constellation parameters.

[0123] Figure 2 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 2 .like Figure 2 As shown, based on the above embodiment, this embodiment provides a supplementary explanation of the process of obtaining the average visible satellite ratio of the ground node in each layer of the satellite constellation in the multi-layer satellite constellation, including:

[0124] S201, determining the geocentric angle corresponding to the visible range of the ground node to the satellite based on the elevation angle parameter of the ground node and the satellite orbit height;

[0125] In this embodiment, the orbital parameters include the satellite orbital altitude, orbital inclination, number of orbital planes, and number of satellites in each orbital plane; the ground node parameters include the latitude parameter and elevation parameter of the ground node.

[0126] Figure 3 A schematic diagram of the visible range of a single-layer low-orbit satellite from an earth node provided in an embodiment of the present application is shown in FIG. Figure 3 As shown, for latitude For a ground node K with an elevation angle of β, its visible range from the satellite sphere (the light-colored portion between Earth and the Satellite sphere) is a spherical cap (the dark portion between Y and Z), with the northernmost end of the cap being point Y and the southernmost end being point Z. The geocentric angle corresponding to the ground node's visible range from the satellite is set to 2θ, which can be obtained as follows:

[0127]

[0128] Among them, θ represents the half geocentric angle corresponding to the visible range of the ground node to the satellite, represents the latitude parameter of the ground node, β represents the elevation parameter of the ground node, R represents the radius of the earth, and h represents the satellite orbit height.

[0129] S202, obtaining multiple position phases corresponding to the visible satellite spherical caps according to the geocentric angle, orbital inclination, and latitude parameters of the ground node;

[0130] In this embodiment, the position phase includes a north phase, a south phase, and a middle phase.

[0131] According to the maximum corresponding geocentric angle 2θ of the visible satellite cap obtained in S201, the orbital inclination α and the latitude parameters of the ground node The latitude of the southernmost point Z of the visible cap can be determined to be The latitude of the northernmost point Y is From this, the phase of the southernmost point Z, the phase of the northernmost point Y and the phase of point K can be obtained respectively as

[0132]

[0133] Among them, Phase Z Represents the phase of the southernmost point Z (south phase), Phase Y Represents the phase of the northernmost point Y (north phase), Phase K represents the phase of the midpoint K (intermediate phase), α represents the orbital inclination, and θ represents half of the geocentric angle corresponding to the visible range of the ground node to the satellite. Represents the latitude parameter of the ground node.

[0134] S203, determining the positional relationship between the orbital inclination and the position phase;

[0135] Figure 4 The schematic diagram of the positional relationship between the visible spherical cap and the satellite distribution range provided in the embodiment of the present application is as follows: Figure 4As shown, the gray circle is the satellite spherical cap visible from the ground node, and the black arc is the northernmost latitude line that the satellite of the single-layer constellation with an inclination angle of α can reach. As the latitude of point K gradually increases from 0 to 90 degrees north latitude, under the premise that the visible spherical cap overlaps with the satellite distribution range, there are three situations in the positional relationship between the visible spherical cap and the satellite distribution range, namely, situation 1: the orbital inclination α is higher than the northern phase Y, situation 2: the orbital inclination α is lower than the northern phase and higher than the intermediate phase K, and situation 3: the orbital inclination α is lower than the intermediate phase K and higher than the southern phase Z.

[0136] S204. If the orbital inclination is higher than the north phase, determine a first phase difference between the upper and lower portions of the satellite spherical cap visible from the ground node based on the position phase; determine a first phase number between the upper and lower portions of the satellite spherical cap visible from the ground node based on the first phase difference and the number of satellites in each orbital plane; and determine a first latitude corresponding to a phase median point based on the orbital inclination, the north phase, the south phase, and the intermediate phase.

[0137] In this embodiment, the upper and lower parts of the satellite spherical cap visible to the ground node each correspond to a first phase difference, and each third phase difference corresponds to a first latitude.

[0138] If the orbital inclination is higher than the north phase, then according to the position phase, the phase difference between the upper and lower parts of the satellite can be determined to be

[0139] ΔPhase1=Phase Y -Phase K , ΔPhase2=Phase K -Phase Z

[0140] Among them, ΔPhase1 represents the phase difference of the upper half of the satellite, and ΔPhase2 represents the phase difference of the lower half of the satellite;

[0141] The number of phases contained in the upper and lower parts are

[0142]

[0143] Among them, N Phase1 Represents the first phase number of the upper half of the satellite, N Phase2 represents the first phase number of the lower half of the satellite, and N represents the number of satellites in each orbital plane in the multi-layer satellite constellation;

[0144] The latitudes corresponding to the midpoints of the phases of the upper and lower parts are

[0145]

[0146] Wherein, λ1 represents the first latitude corresponding to the phase midpoint of the upper half of the satellite, and λ2 represents the first latitude corresponding to the phase midpoint of the lower half of the satellite.

[0147] S205. If the orbital inclination is lower than the north phase and higher than the middle phase, determine, based on the position phase, a second phase difference between the upper and lower portions of the satellite spherical cap visible from the ground node; determine, based on the second phase difference and the number of satellites in each orbital plane, the second phase number of the upper and lower portions of the satellite spherical cap visible from the ground node; and determine, based on the orbital inclination, the north phase, the south phase, and the middle phase, a second latitude corresponding to the phase median point.

[0148] In this embodiment, the upper and lower parts of the satellite spherical cap visible to the ground node each correspond to a second phase difference, and each third phase difference corresponds to a second latitude.

[0149] If the orbital inclination is lower than the north phase and higher than the middle phase, the phase differences between the upper and lower parts of the satellite are

[0150] ΔPhase1=π / 2-Phase K , ΔPhase2=Phase K -Phase Z

[0151] Among them, ΔPhase1 represents the phase difference of the upper half of the satellite, and ΔPhase2 represents the phase difference of the lower half of the satellite;

[0152] The number of phases contained in the upper and lower parts are

[0153]

[0154] Among them, N Phase1 Represents the second phase number of the upper half of the satellite, N Phase2 represents the second phase number of the lower half of the satellite, and N represents the number of satellites in each orbital plane in the multi-layer satellite constellation;

[0155] The latitudes corresponding to the midpoints of the phases of the upper and lower parts are

[0156]

[0157] Wherein, λ1 represents the second latitude corresponding to the phase midpoint of the upper half of the satellite, and λ2 represents the second latitude corresponding to the phase midpoint of the lower half of the satellite.

[0158] S206. If the orbital inclination is lower than the middle phase and higher than the south phase, determine, based on the position phase, a third phase difference between the upper and lower portions of the satellite spherical cap visible from the ground node; determine, based on the third phase difference and the number of satellites in each orbital plane, a third phase number for the upper and lower portions of the satellite spherical cap visible from the ground node; and determine, based on the orbital inclination, the north phase, the south phase, and the middle phase, a third latitude corresponding to the phase median point.

[0159] In this embodiment, the upper and lower parts of the satellite spherical cap visible to the ground node each correspond to a third phase difference, and each third phase difference corresponds to a third latitude.

[0160] If the orbital inclination is lower than the middle phase and higher than the south phase, the phase differences between the upper and lower parts of the satellite are

[0161] ΔPhase1=0, ΔPhase2=π / 2-Phase Z

[0162] Among them, ΔPhase1 represents the phase difference of the upper half of the satellite, and ΔPhase2 represents the phase difference of the lower half of the satellite;

[0163] The number of phases contained in the upper and lower parts are

[0164]

[0165] Among them, N Phase1 Represents the third phase number of the upper half of the satellite, N Phase2 represents the third phase number of the lower half of the satellite, and N represents the number of satellites in each orbital plane in the multi-layer satellite constellation;

[0166] The latitudes corresponding to the midpoints of the phases of the upper and lower parts are

[0167]

[0168] Among them, λ1 represents the third latitude corresponding to the phase midpoint of the upper half of the satellite, and λ2 represents the third latitude corresponding to the phase midpoint of the lower half of the satellite.

[0169] S207, determining the longitude range corresponding to the satellite phase median point based on the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point;

[0170] In this embodiment, the target phase number may be any one of the first phase number, the second phase number, or the third phase number, and the target latitude may be the first latitude, the second phase number, or the third latitude corresponding to the target phase number.

[0171] According to the target phase number of the upper and lower parts of the satellite spherical cap visible to the ground node and the target latitude corresponding to the phase median point, the latitude of the visible spherical cap of the ground node to the satellite spherical shell can be determined to be λ i The longitude range corresponding to the point is

[0172]

[0173] Among them, ΔULon i and 2ρ i Both represent latitude λ i The longitude range corresponding to the point.

[0174] S208. Obtain the corresponding satellite density based on the number of orbital planes, and determine the time average of the number of visible satellites in the single-layer satellite constellation based on the longitude range and satellite density corresponding to the satellite phase median point;

[0175] For the satellite distribution on the satellite sphere, the satellite density at different latitudes can be obtained based on the number of orbital planes, that is,

[0176] π / M

[0177] Where M represents the number of orbital planes of the satellite constellation;

[0178] According to the longitude range and satellite density corresponding to the satellite phase median point, the time average number of visible satellites in a single-layer satellite constellation is determined as

[0179]

[0180] Among them, Sat i Represents the time average of the number of visible satellites in a single-layer satellite constellation, ΔULon i Represents latitude λ i The longitude range corresponding to the point.

[0181] S209: Determine the number of visible satellites in the single-layer satellite constellation based on the latitude parameter of the ground node, the phase numbers of the upper and lower parts of the satellite sphere visible from the ground node, and the time average of the number of visible satellites in the single-layer satellite constellation;

[0182] According to the latitude parameters of the ground node, the phase numbers of the upper and lower parts of the satellite sphere visible from the ground node and the time average of the number of visible satellites in the single-layer satellite constellation, the number of visible satellites in the single-layer satellite constellation is determined as

[0183]

[0184] in, Represents the number of visible satellites in a single-layer satellite constellation, Sat i represents the time average number of visible satellites in a single-layer satellite constellation, N PhaseiThe target phase number representing the upper and lower parts of the satellite cap visible to the ground node.

[0185] S210. Input the longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in a single-layer satellite constellation, and the number of visible satellites in a single-layer satellite constellation into a first target model, and obtain the average visible satellite ratio of ground nodes corresponding to the single-layer satellite constellation output by the first target model.

[0186] In this embodiment, the first target model is a mathematical model for calculating the average ratio of visible satellites from ground nodes corresponding to each single-layer satellite constellation in a multi-layer satellite constellation.

[0187] For each single-layer satellite constellation in the multi-layer satellite constellation, the longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are input into the first target model. The ratio of the average number of visible satellites for ground nodes at different latitudes to the total number of satellites output by the first target model is obtained as follows:

[0188]

[0189] in, Represents the average visible satellite ratio of ground nodes corresponding to a single-layer satellite constellation, represents the number of visible satellites in a single-layer satellite constellation, N represents the number of satellites in each orbital plane in a multi-layer satellite constellation, and M represents the number of orbital planes in the satellite constellation.

[0190] The present application provides a method for obtaining multi-layer satellite constellation parameters, which obtains the longitude range corresponding to the corresponding satellite phase median point, the time average of the number of visible satellites in a single-layer satellite constellation, and the number of visible satellites in a single-layer satellite constellation based on the orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation, so as to obtain the average visible satellite ratio of ground nodes corresponding to each layer of satellite constellations in the multi-layer satellite constellation. By obtaining the average visible satellite ratio of ground nodes corresponding to each layer of satellite constellations in the multi-layer satellite constellation, the latitude position corresponding to the highest coverage of the constellation to the ground can be customized during constellation design to match the access requirements of different regions, thereby improving the flexibility and convenience of the multi-layer satellite constellation parameter acquisition process, avoiding environmental restrictions on the parameter acquisition process, solving the technical problem of low efficiency in acquiring multi-layer satellite constellation parameters, and achieving the technical effect of improving the efficiency of acquiring multi-layer satellite constellation parameters.

[0191] Figure 5 The process of obtaining multi-layer satellite constellation parameters provided in the embodiment of the present application Figure 3 .like Figure 5As shown, this embodiment, based on the above embodiment, provides a supplementary explanation of the process of obtaining the optimal multi-layer satellite constellation parameters, including:

[0192] S501. Obtaining satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters;

[0193] In this embodiment, the satellite configuration parameters include the total number of satellites in all layers, the satellite orbit altitude range and the orbit inclination range, and the basic communication parameters include the receiving power, bandwidth, noise power spectrum density, transmitting end and receiving end antenna gain and satellite wavelength between the ground node and the satellite.

[0194] According to user needs, obtain the satellite configuration parameters to be optimized, ground communication requirements and basic communication parameters.

[0195] S502. Determine the path loss between the ground node and the satellite based on the satellite wavelength and the altitude range of the satellite orbit, and determine the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation based on the path loss, the received power between the ground node and the satellite, the bandwidth, the noise power spectral density, and the transmitter and receiver antenna gains;

[0196] According to the satellite wavelength and the altitude range of the satellite orbit, the path loss between the ground node and the satellite is determined as

[0197]

[0198] Where l represents the path loss between the ground node and the satellite, λ wave represents the satellite wavelength, and h represents the satellite orbit height;

[0199] According to the path loss, the receiving power between the ground node and the satellite, the bandwidth, the noise power spectrum density, the transmitting and receiving antenna gains, and the Shannon formula, the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation is determined as follows:

[0200]

[0201] Among them, C represents capacity, S represents user received power, B represents bandwidth, n0 represents noise power spectrum density, P t Represents the transmitting end power, G r and G t represents the antenna gain of the receiving and transmitting ends, and l represents the path loss;

[0202] Assuming B = 1Hz, then

[0203]

[0204] Among them, C(h) represents the accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation, and P0 represents the user's received power.

[0205] S503. Obtain the minimum number of orbital planes and the minimum number of satellites in each orbital plane for each layer of the multi-layer satellite constellation. Based on the minimum number of orbital planes, the minimum number of satellites in each orbital plane, and the total number of satellites in all layers, obtain the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation.

[0206] Figure 6 A schematic diagram of the positions of adjacent satellites in adjacent orbits in a multi-layer satellite constellation provided in an embodiment of the present application is shown in FIG. Figure 6 As shown, let the total number of satellites in all layers be SatNum. For a multi-layer low-orbit satellite constellation with a total number of satellites being SatNum, points A, B, C, and D in the positions of adjacent satellites in adjacent orbits are four adjacent satellites on two adjacent orbits, and point C' is the intersection of a perpendicular line from point C to the equator and the equator.

[0207] Specifically, when the satellites are at the equator, the spherical quadrilateral formed by the four adjacent satellites in the adjacent orbit has the largest area and the diagonal has the maximum value. When the number of layers is the largest, the satellites in each layer are the sparsest, the satellite altitude is the maximum, and the orbital inclination is the maximum, it is necessary to ensure that the arc AC is less than 2θ. The spherical quadrilateral at the equator is approximated as a spherical parallelogram. When M is approximately equal to N (satellites are evenly distributed) and F = 0, it is approximated as a spherical rhombus. First, calculate the arc AC as follows:

[0208]

[0209] Utilization restrictions

[0210]

[0211] When M is approximately equal to N (satellites are evenly distributed) and F = 0, it can be calculated that when the number of satellites in the multi-layer satellite constellation is SatNum, the maximum number of satellite layers and the minimum proportion of satellites in each layer are

[0212] S max =floor(SatNum / M min / N min )

[0213] ρ min =M min ·N min / SatNum

[0214] Among them, S max Represents the maximum number of satellite layers corresponding to a multi-layer satellite constellation, floor represents the floor rounding function, ρ minRepresents the minimum proportion of satellites in each layer, SatNum represents the total number of satellites in all layers, M min Represents the minimum number of orbital surfaces, N min Represents the minimum number of satellites per orbital plane.

[0215] S504: Input the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of ground nodes into the second target model to obtain the ground coverage capacity corresponding to the multi-layer constellation output by the second target model;

[0216] In this embodiment, the second target model is a mathematical model for calculating the ground coverage capacity of a multi-layer satellite constellation.

[0217] The accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of ground nodes are input into the second target model to obtain the ground coverage corresponding to the multi-layer constellation output by the second target model:

[0218]

[0219] in, represents the ground coverage capacity corresponding to the multi-layer constellation, S represents the maximum number of satellite layers in the multi-layer satellite constellation, represents the average visible satellite ratio of the ground nodes corresponding to the S-layer satellite constellation, αs represents the orbital inclination of the S-layer satellite constellation, and hs represents the satellite orbit height of the S-layer satellite constellation. Represents the latitude range of the ground node, M s Represents the number of orbital planes of the S-layer satellite constellation, N s represents the number of satellites in each orbital plane in the S-layer satellite constellation, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity, SatNum represents the total number of satellites in all layers, ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0220] S505. Determine a corresponding Spearman correlation coefficient based on ground coverage capacity and ground communication requirements;

[0221] For constellation optimization problems, the ground coverage capacity of multi-layer low-orbit satellite constellations Distribution of ground communication needs The Spearman correlation coefficient is

[0222]

[0223] Among them, the distribution of ground communication demand is the input parameter, which is the distribution of ground communication demand with latitude.

[0224] S506. Acquire multiple multi-layer satellite constellations that meet the constellation configuration parameter requirements and constellation parameters of each layer of satellites in each multi-layer satellite constellation, and construct multiple multi-layer satellite constellation parameter matrices based on the constellation parameters of each layer of satellites in each multi-layer satellite constellation;

[0225] In this embodiment, the constellation parameters include satellite altitude, satellite inclination, and satellite ratio of each layer of satellite constellation in each multi-layer satellite constellation. One multi-layer satellite constellation corresponds to one multi-layer satellite constellation parameter matrix.

[0226] According to the satellite configuration parameters to be optimized, multiple multi-layer satellite constellations that meet the constellation configuration parameter requirements are obtained, and for these multi-layer satellite constellations, the satellite altitude, satellite inclination and satellite ratio of each layer of satellites in each multi-layer satellite constellation are obtained, and the satellite altitude, satellite inclination and satellite ratio of each layer of satellites in each multi-layer satellite constellation are summarized to construct a corresponding multi-layer satellite constellation parameter matrix.

[0227] Specifically, a user wants to send 4,000 satellites into space, and these 4,000 satellites are distributed within the altitude range of 1,000 km to 1,200 km. At the same time, the orbital inclination range is between 30° and 60°. Within the user's specified satellite orbit altitude range and inclination range, multiple multi-layer satellite constellations that can accommodate 4,000 satellites are designed. For each multi-layer satellite constellation, the satellite altitude, satellite inclination, and satellite ratio of each layer of satellites in each multi-layer satellite constellation are obtained to construct the corresponding multi-layer satellite constellation parameter matrix.

[0228] S507. According to the sparrow algorithm, multiple multi-layer satellite constellations are aggregated to form a sparrow population, and each multi-layer satellite constellation parameter matrix is ​​used as a position matrix of each sparrow in the sparrow population;

[0229] According to the sparrow algorithm, all satellite constellations that meet user needs are aggregated to form a sparrow population, and the parameter matrix corresponding to each multi-layer satellite constellation is used as the position matrix of each sparrow in the sparrow population. The sparrow position matrix is ​​as follows:

[0230]

[0231] Among them, x(j,s i , 3) represents the position matrix of the sparrow.

[0232] S508. Obtain an initialized sparrow population according to a chaotic mapping algorithm, perform multiple iterative updates on the position matrix of each sparrow in the initialized sparrow population, and obtain a Spearman correlation coefficient corresponding to each sparrow in the sparrow population after each iterative update;

[0233] In this embodiment, one sparrow corresponds to one Spearman correlation coefficient.

[0234] A chaotic mapping algorithm is used to initialize the sparrow population. After initialization, the position matrix of each sparrow in the sparrow population is iteratively updated to obtain the ground coverage capacity corresponding to the multi-layer constellation for each sparrow. Combined with the ground communication requirements, the Spearman correlation coefficient corresponding to each sparrow is determined.

[0235] S509: After determining that the number of iterations reaches the target threshold, obtain the maximum Spearman correlation coefficient in the sparrow population for the current number of iterations, and use the position matrix of the sparrow corresponding to the maximum Spearman correlation coefficient as the optimal multi-layer satellite constellation parameter based on the maximum Spearman correlation coefficient.

[0236] In this embodiment, the optimal multi-layer satellite constellation parameter is an optimal multi-layer satellite constellation parameter matrix in the multi-layer satellite constellation.

[0237] For the sparrow algorithm, when the number of iterative updates reaches the target threshold, the Spearman correlation coefficient of each sparrow in the sparrow population after the current iterative update is obtained for the current number of iterations, the Spearman correlation coefficients of each sparrow are compared, the maximum Spearman correlation coefficient is obtained, and the position parameters of the sparrow corresponding to the maximum Spearman correlation coefficient are determined as the optimal multi-layer satellite constellation parameters in the multi-layer satellite constellation.

[0238] The present application provides a method for obtaining parameters of a multi-layer satellite constellation. The method determines the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, and the minimum satellite ratio of each layer based on the satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters. Furthermore, the method obtains the ground coverage capacity of the multi-layer satellite constellation and the Spearman correlation coefficient between the multi-layer satellite constellation and the ground communication requirements, based on the average visible satellite ratio of ground nodes in each layer of the satellite constellation. Furthermore, the method uses a sparrow algorithm to obtain the multi-layer satellite constellation with the largest Spearman correlation coefficient among multiple multi-layer satellite constellations, and uses the constellation parameters of the multi-layer satellite constellation as the optimal multi-layer satellite constellation parameters. The method thus utilizes the ground coverage capacity and the corresponding Spearman correlation coefficient of the multi-layer satellite constellation to obtain the optimal multi-layer satellite constellation parameters, ensuring the reliability and accuracy of the multi-layer satellite constellation parameters. Furthermore, the method utilizes the sparrow algorithm to improve the convenience of the multi-layer satellite constellation parameter acquisition process, reduce the complexity of the overall calculation process, save time costs, and solve the technical problem of low efficiency in heterogeneous network fusion processing, thereby achieving the technical effect of improving heterogeneous network fusion processing efficiency.

[0239] Figure 7 This is a schematic diagram of the structure of the device for obtaining multi-layer satellite constellation parameters provided in an embodiment of the present application. The device of this embodiment can be in the form of software and / or hardware. Figure 7 As shown, the apparatus 700 for obtaining multi-layer satellite constellation parameters provided in an embodiment of the present application includes: a first processing module 701, a second processing module 702, a third processing module 703, and an obtaining module 704:

[0240] The first processing module 701 is configured to determine multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of the multi-layer satellite constellation to obtain an average ratio of visible satellites from the corresponding ground nodes, wherein the single-layer satellite parameters include the longitude range corresponding to the satellite phase median point, the time average number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation;

[0241] The second processing module 702 is configured to obtain satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters, and determine multiple multi-layer satellite parameters based on the satellite configuration parameters and basic communication parameters. The multi-layer satellite parameters include the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, and the minimum proportion of satellites in each layer.

[0242] The third processing module 703 is configured to obtain the ground coverage capacity of the multi-layer satellite constellation based on the multi-layer satellite parameters, satellite configuration parameters, and the average ratio of visible satellites from ground nodes in each layer of the satellite constellation, and determine the corresponding Spearman correlation coefficient in combination with ground communication requirements;

[0243] The acquisition module 704 is configured to iteratively update the constellation parameters of the multi-layer satellite constellation according to the target optimization algorithm and the Spearman correlation coefficient to obtain the optimal multi-layer satellite constellation parameters, wherein the target optimization algorithm includes the sparrow algorithm and the chaos mapping algorithm.

[0244] In a possible implementation, the first processing module 701 is further configured to:

[0245] According to the elevation angle parameters of the ground node and the satellite orbit height, the geocentric angle corresponding to the visible range of the ground node to the satellite is determined;

[0246] According to the geocentric angle, orbital inclination and latitude parameters of the ground node, multiple position phases corresponding to the visible satellite cap are obtained respectively, where the position phases include the north phase, the south phase and the middle phase;

[0247] Determine the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point based on the positional relationship between the position phase and the orbital inclination, and determine the longitude range corresponding to the satellite phase median point based on the target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point;

[0248] According to the number of orbital planes, the corresponding satellite density is obtained, and according to the longitude range and satellite density corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation is determined;

[0249] The number of visible satellites in a single-layer satellite constellation is determined based on the latitude parameters of the ground node, the phase numbers of the upper and lower parts of the satellite sphere visible from the ground node, and the time average of the number of visible satellites in the single-layer satellite constellation.

[0250] In a possible implementation, the first processing module 701 is further configured to:

[0251] If the orbital inclination is higher than the north phase, determining a first phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node according to the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one first phase difference;

[0252] Determine, based on the first phase difference and the number of satellites in each orbital plane, the first phase numbers of the upper and lower portions of the satellite spherical cap visible from the ground node, and determine, based on the orbital inclination, the north phase, the south phase, and the intermediate phase, the first latitude corresponding to the phase median point, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to a first latitude;

[0253] If the orbital inclination is lower than the north phase and higher than the middle phase, then determining a second phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one second phase difference;

[0254] Determine the second phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node based on the second phase difference and the number of satellites in each orbital plane, and determine the second latitude corresponding to the phase median point based on the orbital inclination, the north phase, the south phase, and the intermediate phase, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a second latitude;

[0255] If the orbital inclination is lower than the middle phase and higher than the south phase, then determine the third phase difference between the upper and lower parts of the satellite spherical cap visible from the ground node based on the position phase, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one third phase difference;

[0256] According to the third phase difference and the number of satellites in each orbital plane, the third phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node are determined, and according to the orbital inclination, north phase, south phase and intermediate phase, the third latitude corresponding to the phase median point is determined, where the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to a third latitude.

[0257] In a possible implementation, the first processing module 701 is further configured to:

[0258] The longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in a single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are input into a first target model to obtain an average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation output by the first target model. The first target model is a mathematical model for calculating the average ratio of visible satellites for ground nodes corresponding to each single-layer satellite constellation in a multi-layer satellite constellation. The average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation is achieved by the following method:

[0259]

[0260] in, Represents the average visible satellite ratio of ground nodes corresponding to a single-layer satellite constellation, represents the number of visible satellites in a single-layer satellite constellation, M represents the number of orbital planes, N represents the number of satellites in each orbital plane, α represents the orbital inclination, and h represents the satellite orbit height. represents the latitude parameter of the ground node, i represents the upper and lower parts of the satellite cap visible from the ground node, ΔPhase i Represents the phase difference between the upper and lower parts of the satellite cap visible to the ground node, λ irepresents the target latitude corresponding to the phase median point, and β represents the elevation angle parameter of the ground node.

[0261] In a possible implementation, the second processing module 702 is further configured to:

[0262] Determine the path loss between the ground node and the satellite based on the satellite wavelength and the altitude range of the satellite orbit;

[0263] Determine the accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation based on path loss, received power between ground nodes and satellites, bandwidth, noise power spectral density, and transmitter and receiver antenna gains;

[0264] Get the minimum number of orbital planes and the minimum number of satellites in each orbital plane for each layer in a multi-layer satellite constellation. Based on the minimum number of orbital planes, the minimum number of satellites in each orbital plane, and the total number of satellites in all layers, get the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation. The maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation are obtained in the following way:

[0265] S max =floor(SatNum / M min / N min )

[0266] ρ min =M min ·N min / SatNum

[0267] Among them, S max Represents the maximum number of satellite layers corresponding to a multi-layer satellite constellation, floor represents the floor rounding function, ρ min Represents the minimum proportion of satellites in each layer, SatNum represents the total number of satellites in all layers, M min Represents the minimum number of orbital surfaces, N min Represents the minimum number of satellites per orbital plane.

[0268] In a possible implementation, the third processing module 703 is further configured to:

[0269] The accessible capacity corresponding to satellites at different altitudes in a multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of ground nodes are input into a second target model to obtain the ground coverage capacity corresponding to the multi-layer constellation output by the second target model. The second target model is a mathematical model for calculating the ground coverage capacity of the multi-layer satellite constellation. The ground coverage capacity corresponding to the multi-layer satellite constellation is achieved by the following method:

[0270]

[0271] in, represents the ground coverage capacity corresponding to the multi-layer constellation, S represents the maximum number of satellite layers in the multi-layer satellite constellation, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, M s Represents the number of orbital planes of the S-layer satellite constellation, N s represents the number of satellites in each orbital plane in the S-layer satellite constellation, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity, SatNum represents the total number of satellites in all layers, ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0272] In a possible implementation, the third processing module 703 is further configured to:

[0273] According to the ground coverage capacity and ground communication requirements, the corresponding Spearman correlation coefficient is determined and obtained by the following method:

[0274]

[0275] in, represents the Spearman correlation coefficient, Represents the ground coverage capacity corresponding to the multi-layer constellation, represents the distribution of ground communication demand, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity is ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

[0276] In a possible implementation, the obtaining module 704 is further configured to:

[0277] Acquire multiple multi-layer satellite constellations that meet constellation configuration parameter requirements and constellation parameters of each layer of satellites in each multi-layer satellite constellation, and construct multiple multi-layer satellite constellation parameter matrices based on the constellation parameters of each layer of satellites in each multi-layer satellite constellation, wherein the constellation parameters include satellite altitude, satellite inclination, and satellite ratio of each layer of satellite constellation in each multi-layer satellite constellation, and one multi-layer satellite constellation corresponds to one multi-layer satellite constellation parameter matrix;

[0278] According to the sparrow algorithm, multiple multi-layer satellite constellations are aggregated as a sparrow population, and each multi-layer satellite constellation parameter matrix is ​​used as the position matrix of each sparrow in the sparrow population;

[0279] According to the chaotic mapping algorithm, an initialized sparrow population is obtained, and the position matrix of each sparrow in the initialized sparrow population is iteratively updated multiple times. After each iterative update, the Spearman correlation coefficient corresponding to each sparrow in the sparrow population is obtained, wherein one sparrow corresponds to one Spearman correlation coefficient;

[0280] After determining that the number of iterations reaches the target threshold, the maximum Spearman correlation coefficient in the sparrow population is obtained for the current number of iterations, and based on the maximum Spearman correlation coefficient, the position matrix of the sparrow corresponding to the maximum Spearman correlation coefficient is used as the optimal multi-layer satellite constellation parameter.

[0281] The present application provides a device for obtaining multi-layer satellite constellation parameters, which can implement the above method embodiment. Its implementation principle and technical effects are similar, and this embodiment will not be repeated here.

[0282] Figure 8 This is a hardware structure diagram for obtaining multi-layer satellite constellation parameters provided in the embodiment of this application. Figure 8 As shown, the multi-layer satellite constellation parameter acquisition device 800 includes:

[0283] Processor 801 and memory 802;

[0284] Memory stores computer-executable instructions;

[0285] The processor executes the computer-executable instructions stored in the memory 802, so that the device for obtaining multi-layer satellite constellation parameters executes the method for obtaining multi-layer satellite constellation parameters as described above.

[0286] It should be understood that the processor 801 can be a central processing unit (CPU), other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), etc. A general-purpose processor can be a microprocessor or any conventional processor. The steps of the method disclosed in the present invention can be directly implemented by a hardware processor or by a combination of hardware and software modules in the processor.

[0287] The memory 802 may include a high-speed random access memory (RAM) and may also include a non-volatile memory (NVM), such as at least one disk memory, and may also be a USB flash drive, a mobile hard disk, a read-only memory, a magnetic disk, or an optical disk.

[0288] An embodiment of the present application correspondingly provides a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, they are used to implement the method for obtaining multi-layer satellite constellation parameters as described above.

[0289] The embodiments of the present application also provide a computer program product, which, when executed by a processor, is used to implement the above-mentioned method for obtaining multi-layer satellite constellation parameters.

[0290] It should be noted that for the aforementioned method embodiments, for the sake of simplicity, they are all expressed as a series of action combinations, but those skilled in the art should be aware that this application is not limited by the order of the actions described, because according to this application, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in this specification are all optional embodiments, and the actions and modules involved are not necessarily required by this application.

[0291] It should be further noted that, although the various steps in the flowchart are shown in sequence as indicated by the arrows, these steps are not necessarily performed in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order restriction on the execution of these steps, and these steps may be performed in other orders. Moreover, at least a portion of the steps in the flowchart may include multiple sub-steps or multiple stages, and these sub-steps or stages are not necessarily performed at the same time, but may be performed at different times. The execution order of these sub-steps or stages is not necessarily to be performed in sequence, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.

[0292] It should be understood that the above-described device embodiments are merely illustrative, and the device of the present application may also be implemented in other ways. For example, the division of units / modules in the above-described embodiments is merely a logical functional division, and actual implementations may employ other division methods. For example, multiple units, modules, or components may be combined or integrated into another system, or some features may be omitted or not implemented.

[0293] In addition, unless otherwise specified, the functional units / modules in the various embodiments of the present application may be integrated into a single unit / module, each unit / module may exist physically separately, or two or more units / modules may be integrated together. The aforementioned integrated units / modules may be implemented in the form of hardware or software program modules.

[0294] If the integrated unit / module is implemented in hardware, the hardware may be digital circuits, analog circuits, etc. The physical implementation of the hardware structure includes, but is not limited to, transistors, memristors, etc. Unless otherwise specified, the processor may be any appropriate hardware processor, such as a CPU, GPU, FPGA, DSP, and ASIC. Unless otherwise specified, the storage unit may be any appropriate magnetic storage medium or magneto-optical storage medium, such as resistive random access memory (RRAM), dynamic random access memory (DRAM), static random access memory (SRAM), enhanced dynamic random access memory (EDRAM), high-bandwidth memory (HBM), hybrid memory cube (HMC), etc.

[0295] If the integrated unit / module is implemented in the form of a software program module and sold or used as an independent product, it can be stored in a computer-readable memory. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product, which is stored in a memory and includes a number of instructions for enabling a computer device (which can be a personal computer, server or network device, etc.) to execute all or part of the steps of the various embodiments of the present application. The aforementioned memory includes various media that can store program codes, such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk.

[0296] In the above embodiments, the description of each embodiment has its own emphasis. For parts not described in detail in a particular embodiment, please refer to the relevant description of other embodiments. The technical features of the above embodiments can be combined in any way. To keep the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0297] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present application that follow the general principles of the present application and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only, and the true scope and spirit of the present application are indicated by the following claims.

[0298] It should be understood that the present application is not limited to the exact structure described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. A method for obtaining multi-layer satellite constellation parameters, characterized in that: include: Determine multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation to obtain an average visible satellite ratio of the corresponding ground nodes, wherein the single-layer satellite parameters include a longitude range corresponding to a satellite phase median point, a time average of the number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation; Obtaining satellite configuration parameters to be optimized, ground communication requirements, and basic communication parameters, and determining multiple multi-layer satellite parameters based on the satellite configuration parameters and the basic communication parameters, wherein the multi-layer satellite parameters include accessible capacities corresponding to satellites at different altitudes in a multi-layer satellite constellation, a maximum number of satellite layers corresponding to the multi-layer satellite constellation, and a minimum proportion of satellites in each layer; Obtaining, based on the multi-layer satellite parameters, the satellite configuration parameters, and the average ratio of visible satellites from the ground nodes of each layer of the satellite constellation, a ground coverage capacity of the multi-layer satellite constellation, and determining a corresponding Spearman correlation coefficient in combination with the ground communication demand; According to a target optimization algorithm and the Spearman correlation coefficient, constellation parameters of the multi-layer satellite constellation are iteratively updated to obtain optimal multi-layer satellite constellation parameters, wherein the target optimization algorithm includes a sparrow algorithm and a chaos mapping algorithm.

2. The method according to claim 1, characterized in that The orbital parameters include satellite orbit altitude, orbital inclination, number of orbital planes, and number of satellites in each orbital plane; the ground node parameters include latitude parameters and elevation parameters of the ground node; and determining multiple single-layer satellite parameters based on the orbital parameters and ground node parameters of each layer of satellite constellations in the multi-layer satellite constellation includes: Determining the geocentric angle corresponding to the visible range of the ground node to the satellite based on the elevation angle parameter of the ground node and the satellite orbit height; According to the geocentric angle, the orbital inclination, and the latitude parameter of the ground node, a plurality of position phases corresponding to the visible satellite spherical cap are respectively obtained, wherein the position phases include a north phase, a south phase, and an intermediate phase; Determining, based on a positional relationship between the position phase and the orbital inclination, target phase numbers for upper and lower portions of a satellite spherical cap visible from a ground node and a target latitude corresponding to a phase median point, and determining, based on the target phase numbers for upper and lower portions of a satellite spherical cap visible from the ground node and the target latitude corresponding to the phase median point, a longitude range corresponding to the satellite phase median point; Obtaining a corresponding satellite density according to the number of orbital planes, and determining a time average of the number of visible satellites in the single-layer satellite constellation according to the longitude range corresponding to the satellite phase median point and the satellite density; The number of visible satellites of the single-layer satellite constellation is determined according to the latitude parameter of the ground node, the phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node, and the time average of the number of visible satellites of the single-layer satellite constellation.

3. The method according to claim 2, characterized in that Determining, based on the positional relationship between the position phase and the orbital inclination, target phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node and a target latitude corresponding to a phase median point includes: If the orbital inclination is higher than the north phase, determining a first phase difference between an upper and lower portion of a satellite spherical cap visible from the ground node according to the position phase, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to one first phase difference; Determining, based on the first phase difference and the number of satellites in each orbital plane, first phase numbers of upper and lower portions of a satellite spherical cap visible from the ground node, and determining, based on the orbital inclination, the north phase, the south phase, and the intermediate phase, a first latitude corresponding to a phase median point, wherein each of the upper and lower portions of the satellite spherical cap visible from the ground node corresponds to one first latitude; If the orbital inclination is lower than the north phase and higher than the middle phase, determining, based on the position phase, a second phase difference between an upper and lower portion of a satellite spherical cap visible from the ground node, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to one second phase difference; Determining, based on the second phase difference and the number of satellites in each orbital plane, second phase numbers of the upper and lower portions of a spherical cap of satellites visible from the ground node, and determining, based on the orbital inclination, the north phase, the south phase, and the intermediate phase, a second latitude corresponding to the phase median point, wherein the upper and lower portions of the spherical cap of satellites visible from the ground node each correspond to one second latitude; If the orbital inclination is lower than the middle phase and higher than the south phase, determining, based on the position phase, a third phase difference between the upper and lower portions of the satellite spherical cap visible from the ground node, wherein the upper and lower portions of the satellite spherical cap visible from the ground node each correspond to one third phase difference; According to the third phase difference and the number of satellites in each orbital plane, the third phase numbers of the upper and lower parts of the satellite spherical cap visible from the ground node are determined, and according to the orbital inclination, the north phase, the south phase and the intermediate phase, the third latitude corresponding to the phase median point is determined, wherein the upper and lower parts of the satellite spherical cap visible from the ground node each correspond to one third latitude.

4. The method according to claim 3, characterized in that Obtaining the average visible satellite ratio of the corresponding ground node includes: The longitude range corresponding to the satellite phase median point, the time average of the number of visible satellites in the single-layer satellite constellation, and the number of visible satellites in the single-layer satellite constellation are input into a first target model to obtain an average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation output by the first target model. The first target model is a mathematical model for calculating the average ratio of visible satellites for ground nodes corresponding to each single-layer satellite constellation in the multi-layer satellite constellation. The average ratio of visible satellites for ground nodes corresponding to the single-layer satellite constellation is achieved by: in, represents the average visible satellite ratio of the ground nodes corresponding to the single-layer satellite constellation, represents the number of visible satellites in the single-layer satellite constellation, M represents the number of orbital planes, N represents the number of satellites in each orbital plane, α represents the orbital inclination, and h represents the satellite orbit altitude. represents the latitude parameter of the ground node, i represents the upper and lower parts of the satellite cap visible from the ground node, ΔPhase i represents the phase difference between the upper and lower parts of the satellite cap visible to the ground node, λ i represents the target latitude corresponding to the phase median point, and β represents the elevation angle parameter of the ground node.

5. The method according to claim 4, characterized in that The satellite configuration parameters include the total number of satellites in all layers, the satellite orbit altitude range, and the orbit inclination range; the basic communication parameters include the receiving power, bandwidth, noise power spectrum density, transmitting end and receiving end antenna gain, and satellite wavelength between the ground node and the satellite; and the determination of multiple layers of satellite parameters based on the satellite configuration parameters and the basic communication parameters includes: determining a path loss between the ground node and the satellite based on the satellite wavelength and the altitude range of the satellite orbit; Determining, based on the path loss, the received power between the ground node and the satellite, the bandwidth, the noise power spectral density, and the antenna gains of the transmitter and receiver, the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation; Obtaining the minimum number of orbital planes for each layer in a multi-layer satellite constellation and the minimum number of satellites in each orbital plane; obtaining the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation based on the minimum number of orbital planes, the minimum number of satellites in each orbital plane, and the total number of satellites in all layers; the maximum number of satellite layers and the minimum proportion of satellites in each layer corresponding to the multi-layer satellite constellation are obtained by: S max =floor(SatNum / M min / N min ) r min =M min ·N min / SatNum Among them, S max represents the maximum number of satellite layers corresponding to the multi-layer satellite constellation, floor represents the floor rounding function, ρ min Represents the minimum proportion of satellites in each layer, SatNum represents the total number of satellites in all layers, M min Represents the minimum number of orbital planes, N min Represents the minimum number of satellites per orbital plane.

6. The method according to claim 5, characterized in that The obtaining, according to the multi-layer satellite parameters, the satellite configuration parameters, and the average ratio of visible satellites of the ground nodes in each layer of the satellite constellation, the ground coverage capacity of the multi-layer satellite constellation includes: Input the accessible capacity corresponding to satellites at different altitudes in the multi-layer satellite constellation, the maximum number of satellite layers corresponding to the multi-layer satellite constellation, the minimum proportion of satellites in each layer, the satellite orbit altitude range, the orbit inclination range, and the average visible satellite ratio of the ground node into a second target model, and obtain the ground coverage capacity corresponding to the multi-layer satellite constellation output by the second target model, wherein the second target model is a mathematical model for calculating the ground coverage capacity of the multi-layer satellite constellation, and the ground coverage capacity corresponding to the multi-layer satellite constellation is achieved by: in, represents the ground coverage capacity corresponding to the multi-layer constellation, S represents the maximum number of satellite layers in the multi-layer satellite constellation, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, Represents the latitude range of the ground node, M s Represents the number of orbital planes of the S-layer satellite constellation, N s represents the number of satellites in each orbital plane in the S-layer satellite constellation, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity, SatNum represents the total number of satellites in all layers, ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

7. The method according to claim 6, characterized in that The corresponding Spearman correlation coefficient is determined according to the ground coverage capacity and the ground communication requirement, and is obtained in the following manner: in, represents the Spearman correlation coefficient, represents the ground coverage capacity corresponding to the multi-layer constellation, represents the distribution of ground communication demand, represents the average visible satellite ratio of ground nodes corresponding to the S-layer satellite constellation, α s represents the orbital inclination of the S-layer satellite constellation, h s represents the satellite orbit altitude of the S-tier satellite constellation, represents the latitude range of the ground node, C(h s ) represents the satellite orbit height of the S-layer satellite constellation is h s The corresponding accessible capacity is ρ s Represents the minimum percentage of satellites in the S-tier satellite constellation.

8. The method according to claim 7, characterized in that The iteratively updating the constellation parameters of the multi-layer satellite constellation according to the target optimization algorithm and the Spearman correlation coefficient to obtain optimal multi-layer satellite constellation parameters includes: Acquire multiple multi-layer satellite constellations that meet the constellation configuration parameter requirements and constellation parameters of each layer of satellites in each of the multi-layer satellite constellations, and construct multiple multi-layer satellite constellation parameter matrices based on the constellation parameters of each layer of satellites in each of the multi-layer satellite constellations, wherein the constellation parameters include satellite altitude, satellite inclination, and satellite ratio of each layer of satellite constellations in each of the multi-layer satellite constellations, and one multi-layer satellite constellation corresponds to one multi-layer satellite constellation parameter matrix; According to the sparrow algorithm, a plurality of the multi-layer satellite constellations are aggregated to form a sparrow population, and each multi-layer satellite constellation parameter matrix is ​​used as a position matrix of each sparrow in the sparrow population; According to the chaotic mapping algorithm, an initialized sparrow population is obtained, and a position matrix of each sparrow in the initialized sparrow population is iteratively updated multiple times, and after each iterative update, the Spearman correlation coefficient corresponding to each sparrow in the sparrow population is obtained, wherein one Spearman correlation coefficient corresponds to one sparrow; After determining that the number of iterations reaches the target threshold, for the current number of iterations, the maximum Spearman correlation coefficient in the sparrow population is obtained, and based on the maximum Spearman correlation coefficient, the position matrix of the sparrows corresponding to the maximum Spearman correlation coefficient is used as the optimal multi-layer satellite constellation parameter.

9. A device for acquiring multi-layer satellite constellation parameters, characterized in that: include: Memory, processor; The memory stores computer-executable instructions; The processor executes the computer-executable instructions stored in the memory, so that the processor performs the method according to any one of claims 1 to 8.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer-executable instructions, which are used to implement the method according to any one of claims 1 to 8 when executed by a processor.

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