Satellite antenna weight generation method and device, medium and electronic equipment

Abstract

The invention discloses a satellite antenna weight generation method and device, a medium and electronic equipment. The method comprises the following steps: acquiring a boundary vertex set of a target area in the earth in a preset earth-centered earth-fixed coordinate system; converting vertex position coordinates of each boundary vertex in the boundary vertex set into angle coordinates in a satellite earth plane coordinate system; fitting the shape of the target area according to the angle coordinates of the boundary vertexes in the satellite local earth plane coordinate system to obtain a fitted satellite beam projection contour; and generating a satellite antenna weight suitable for the target area based on the fitted satellite beam projection contour. Therefore, when the embodiment of the invention is applied to a non-synchronous satellite squint service scene, beam pattern deformation is not easily caused, inter-cell interference can be reduced, and meanwhile, stable service quality of users in cells can be ensured.

Description

Technical Field

[0001] The present application relates to the field of satellite communication technology, and in particular to a method, device, medium and electronic equipment for generating antenna weights of a satellite. Background Art

[0002] Satellite communication systems usually use onboard phased array antennas to achieve directional shaping of beams to cover specific ground areas. However, due to the influence of satellite orbit altitude and earth curvature, when the 3dB width of the beam (i.e., the width at which the signal strength drops to half of the maximum value) remains unchanged, as the beam points away from the sub-satellite point (i.e., the ground point directly below the satellite), the projection area of ​​the beam on the ground will continue to expand, that is, as the angle between the satellite beam and the ground horizontal line decreases, the projection radius of the beam on the ground will continue to increase, resulting in an increase in the area covered by the beam.

[0003] As the beam projection area continues to expand, the energy of the beam may spread to the adjacent beam service area, resulting in signal overlap. Signal overlap will cause multiple beams to send signals to the same ground area at the same time, which will cause mutual interference between signals. In order to reduce interference between beams, the satellite can use the beamforming capability of the onboard phased array antenna to adjust the antenna weights in real time according to the dynamic changes of the satellite to optimize the shape and direction of the beam, achieve precise coverage of the ground area, and reduce interference between beams.

[0004] The existing satellite beam projection shape design scheme is mainly aimed at geostationary synchronous orbit satellites, and does not fully consider the impact of satellite attitude and satellite motion. When applied to non-synchronous satellite squint service scenarios, it is easy to cause beam pattern deformation and generate inter-beam interference. At the same time, due to the error between the fitted beam pattern and the target service cell contour, it is difficult to ensure the stable service quality of users in the cell. Summary of the invention

[0005] The embodiments of the present application provide a method, device, medium and electronic device for generating antenna weights of a satellite. In order to have a basic understanding of some aspects of the disclosed embodiments, a simple summary is given below. This summary is not a general review, nor is it intended to identify key / important components or describe the scope of protection of these embodiments. Its only purpose is to present some concepts in a simple form as a preface to the detailed description that follows.

[0006] In a first aspect, an embodiment of the present application provides a method for generating antenna weights of a satellite, the method comprising: In a preset Earth-centered Earth-fixed coordinate system, a set of boundary vertices of a target area in the Earth is obtained; The vertex position coordinates of each boundary vertex in the boundary vertex set are converted into angular coordinates in the satellite local surface coordinate system; In the satellite local surface coordinate system, the shape of the target area is fitted according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain a fitted satellite beam projection profile; Based on the fitted satellite beam projection profile, satellite antenna weights suitable for the target area are generated.

[0007] Optionally, the vertex position coordinates are converted to angular coordinates in the satellite's local surface coordinate system, including: In a preset Earth-centered Earth-fixed coordinate system, obtaining satellite position coordinates and satellite velocity vector of the satellite; Calculate, according to the satellite velocity vector, a first unit vector of the satellite local rectangular coordinate system X-axis based on the satellite position coordinate and a second unit vector of the satellite local rectangular coordinate system Z-axis based on the satellite position coordinate; Calculate the vector product between the first unit vector and the second unit vector to obtain a third unit vector of the Y axis of the satellite local rectangular coordinate system based on the satellite position coordinates; Calculate rectangular coordinates according to the vertex position coordinates, the satellite position coordinates, the first unit vector, the second unit vector, and the third unit vector; Based on the rectangular coordinates, a coordinate representation of the vertex position coordinates in the satellite local terrestrial coordinate system is generated as the angular coordinates of each boundary vertex in the satellite local terrestrial coordinate system.

[0008] Optionally, the directions of the X-axis and the Z-axis are set according to the direction of satellite movement and the direction from the satellite to the center of the earth, respectively. The direction of the Y-axis is determined using the right-hand rule. The origin of the satellite's local surface coordinate system is the satellite position coordinate. The coordinate representation includes a target vector calculated based on rectangular coordinates and an azimuth and elevation angle of the vertex position coordinate relative to the satellite position coordinate.

[0009] Optionally, the shape of the target area is fitted according to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system to obtain a fitted satellite beam projection profile, including: According to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system, the characteristic parameters of the ellipse corresponding to the target area are calculated; Based on the binary search method and the characteristic parameters of the ellipse, the satellite beam projection profile is designed to fit the shape of the target area, and the fitted satellite beam projection profile is obtained.

[0010] Optionally, the characteristic parameters of the ellipse include the coordinates of the center point of the ellipse, the rotation angle, and the semi-major axis; Based on the binary search method and the characteristic parameters of the ellipse, the satellite beam projection profile is designed to fit the shape of the target area, and the fitted satellite beam projection profile is obtained, including: According to the center point coordinates, rotation angle and semi-major axis, the minimum semi-minor axis of the ellipse is obtained by binary search method; Generate a half-power beam width profile of a beam area shape required for a target area according to the center point coordinates, the rotation angle, the semi-major axis and the minimum semi-minor axis; The half-power beam width profile of the beam area shape required for the target area is used as the fitted satellite beam projection profile.

[0011] Optionally, the designed shape also includes an elliptical transition region, which is used to fit the main lobe attenuation region, and the elliptical transition region is obtained by proportionally enlarging the fitted satellite beam projection profile; The method also includes: Based on the satellite beam projection profile, a normalized beam gain pattern is generated; wherein the normalized beam gain pattern includes a half-power beam width region corresponding to the satellite beam projection profile, a main lobe attenuation region corresponding to the elliptical transition region, and a side lobe region.

[0012] Optionally, based on the fitted satellite beam projection profile, satellite antenna weights suitable for the target area are generated, including: Define the tap weights of a two-dimensional finite impulse response; Applying Hermitian symmetry to the tap weights to symmetrically process the weight coefficients of the satellite's antenna array to obtain target tap weights; obtaining a tap weight magnitude response of a target tap weight; Establishing a one-to-one mapping relationship between the tap weight amplitude response and the normalized beam gain pattern of the satellite beam projection profile, the mapping relationship being a one-to-one conversion between the azimuth angle and the elevation angle in the normalized beam gain pattern and the antenna weights of the satellite phased array in the X-axis and Y-axis directions; Based on the mapping relationship and a preset inverse fast Fourier transform algorithm, the satellite antenna weights suitable for the target area are calculated.

[0013] In a second aspect, an embodiment of the present application provides a device for generating antenna weights of a satellite, the device comprising: An acquisition module, used to acquire a set of boundary vertices of a target area in the earth in a preset earth-centered earth-fixed coordinate system; A conversion module, used for converting the vertex position coordinates of each boundary vertex in the boundary vertex set into the angular coordinates in the satellite local surface coordinate system; A fitting module is used to fit the shape of the target area in the satellite local surface coordinate system according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain a fitted satellite beam projection profile; The generating module is used to generate satellite antenna weights suitable for the target area based on the fitted satellite beam projection profile.

[0014] In a third aspect, an embodiment of the present application provides a computer storage medium, which stores a plurality of instructions, and the instructions are suitable for being loaded by a processor and executing the above-mentioned method steps.

[0015] In a fourth aspect, an embodiment of the present application provides an electronic device, which may include: a processor and a memory; wherein the memory stores a computer program, and the computer program is suitable for being loaded by the processor and executing the above-mentioned method steps.

[0016] The technical solution provided by the embodiments of the present application may have the following beneficial effects: In order to obtain stable receiving power within a certain area and overcome inter-beam interference caused by satellite beam deformation, this application uses low-complexity regional projection fitting and non-iterative antenna weight calculation to quickly generate satellite beam shapes, solve the problem of the inability to quickly generate adaptive beam areas in existing solutions, and reduce the impact of the high dynamic characteristics of satellites. At the same time, through the designed coordinate transformation and beam area design, the interference caused by beam deformation is reduced. When applied to asynchronous satellite squint service scenarios, it is not easy to cause beam pattern deformation, which can reduce interference between cells and ensure stable service quality for users in the cell.

[0017] This application can support different satellites in the network at different times to quickly determine the coordinates of the target area boundary or the position of the user in the area in the satellite observation coordinate system.

[0018] The present application can design a desired beam area shape based on the obtained coordinate information.

[0019] The present application provides a solution for calculating antenna array element weights based on a given desired beam projection.

[0020] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] 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.

[0022] Figure 1 It is a flowchart of a method for generating antenna weights of a satellite provided in an embodiment of the present application; Figure 2 It is a relationship diagram between the satellite and the target area position provided by this application; Figure 3 It is a structural schematic diagram of a satellite antenna weight generation device provided in an embodiment of the present application; Figure 4It is a structural schematic diagram of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0023] The following description and the accompanying drawings sufficiently illustrate specific embodiments of the present application to enable those skilled in the art to practice them.

[0024] It should be clear that the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0025] When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. Instead, they are only examples of devices and methods consistent with some aspects of the present application as detailed in the attached claims.

[0026] In the description of the present application, it should be understood that the terms "first", "second", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances. In addition, in the description of the present application, unless otherwise specified, "multiple" refers to two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the objects associated before and after are in an "or" relationship.

[0027] The present application provides a method, device, medium and electronic device for generating antenna weights of a satellite to solve the problems existing in the above-mentioned related technical problems. In the embodiment of the present application, in order to obtain stable receiving power within a certain area and overcome the inter-beam interference caused by satellite beam deformation, the present application adopts low-complexity regional projection fitting and non-iterative antenna weight calculation, which can quickly generate the satellite beam shape, solve the problem that the adaptation beam area cannot be quickly generated in the existing solution, and reduce the impact of the high dynamic characteristics of the satellite. At the same time, through the designed coordinate transformation and beam area design, the interference problem caused by beam deformation is reduced. When applied to the asynchronous satellite squint service scenario, it is not easy to cause beam pattern deformation, and inter-beam interference will not occur. At the same time, there is no error between the fitted beam pattern and the expected beam pattern, which can ensure the service quality of users at the edge of the ground area. The following is a detailed description using an exemplary embodiment.

[0028] The following will be combined with the attached Figure 1 -Attached Figure 2 , a method for generating antenna weights for a satellite provided in an embodiment of the present application is introduced in detail. The method can be implemented by a computer program and can be run on a device for generating antenna weights for a satellite based on a von Neumann system. The computer program can be integrated into an application or run as an independent tool application.

[0029] See also Figure 1 , which is a flow chart of a method for generating antenna weights of a satellite according to an embodiment of the present application. Figure 1 As shown, the method of the embodiment of the present application may include the following steps: S101, obtaining a set of boundary vertices of a target area in the earth in a preset earth-centered earth-fixed coordinate system; Among them, ECEF (Earth-Centered, Earth-Fixed) is a three-dimensional Cartesian coordinate system with the center of mass (center of the earth) as the origin, and the coordinate axes point to fixed points on the surface of the earth. This coordinate system is widely used in fields such as earth science, geographic information system (GIS), aerospace, and satellite navigation. ECEF includes: X-axis: usually points to a point on the equator, such as the prime meridian through Greenwich, England, Y-axis: located in the equatorial plane, perpendicular to the X-axis, usually pointing to the meridian of 90 degrees east longitude, Z-axis: perpendicular to the equatorial plane, pointing to the North Pole. The target area refers to a geographic area that requires special attention or service, such as a specific area that needs to be covered in satellite communications. The boundary vertex set is a set of vertices on the boundary of the target area, which defines the outline or shape of the target area.

[0030] In some embodiments, the specific geographic location and range of the target area are first defined to obtain geographic information of the target area, which may include terrain data, map data or other geographic information system (GIS) data, and then the geographic data is analyzed to identify the boundary of the target area and determine the vertices on the boundary. These vertices can be naturally formed landmarks, such as the intersection of mountains and rivers, or artificially defined, such as the boundary points of administrative divisions, and the geographic coordinates (such as latitude and longitude) of these boundary vertices are converted into coordinates in the Earth-centered Earth-fixed coordinate system. For example, the geographic coordinates are converted into X, Y, and Z coordinates in the ECEF coordinate system, and the converted coordinate values ​​are recorded to form a boundary vertex set.

[0031] S102, converting the vertex position coordinates of each boundary vertex in the boundary vertex set into angular coordinates in the satellite local surface coordinate system; The specific position of each boundary vertex in a certain coordinate system is usually expressed as a set of values, such as longitude and latitude or Cartesian coordinates. The directions of the X-axis and Z-axis of the satellite's local surface coordinate system are set according to the direction of the satellite's motion and the direction from the satellite to the center of the earth, respectively. The direction of the Y-axis is determined by the right-hand rule. The origin of the satellite's local surface coordinate system is the satellite position coordinate. The coordinate representation includes the target vector calculated based on rectangular coordinates and the azimuth and elevation of the vertex position coordinate relative to the satellite position coordinate.

[0032] In the embodiment of the present application, after obtaining the vertex position coordinates of each boundary vertex in the boundary vertex set, a satellite local surface coordinate system can be defined, with the satellite position as the origin, and a suitable axis alignment method can be selected. The ECEF coordinates are converted into coordinates in the satellite local surface coordinate system through an algorithm.

[0033] For example, define Target area The boundary vertex set of , where the vertex coordinates are known. By using the specific algorithm processing process of converting the vertex position coordinates into the angular coordinates in the satellite local surface coordinate system, each vertex can be obtained. The angular coordinates in the satellite's local surface coordinate system are expressed as , .

[0034] In some embodiments, the specific algorithm processing process of converting the vertex position coordinates into the angular coordinates in the satellite's local surface coordinate system includes: obtaining the satellite position coordinates and the satellite velocity vector of the satellite in a preset geocentric Earth-fixed coordinate system; calculating the first unit vector of the satellite's local rectangular coordinate system X-axis based on the satellite position coordinates and the second unit vector of the satellite's local surface coordinate system Z-axis based on the satellite position coordinates according to the satellite velocity vector; calculating the vector product between the first unit vector and the second unit vector to obtain the third unit vector of the satellite's local rectangular coordinate system Y-axis based on the satellite position coordinates; calculating the rectangular coordinates according to the vertex position coordinates, the satellite position coordinates and the first unit vector, the second unit vector and the third unit vector; based on the rectangular coordinates, generating the coordinate representation of the vertex position coordinates in the satellite's local surface coordinate system as the angular coordinates of each boundary vertex in the satellite's local surface coordinate system.

[0035] For example Figure 2 As shown, the normal of the phased array antenna passes through the center of the earth. For any vertex, the coordinate transformation is as follows: definition and They are the satellites in the preset Earth Centered Earth Fixed (ECEF) coordinate system. Satellite position coordinates and satellite velocity vector. and The axis directions are set as satellite Direction of movement and satellite The direction to the center of the Earth. Given the satellite velocity vector Down, The axis is based on the unit vector of the dynamic satellite position and is denoted by .at the same time The unit vector of the axis is ,in In addition, satellite Local rectangular coordinate system The direction of the axis is determined by the right-hand rule, and its unit vector , which can be determined by and The vector product between is calculated as: ; definition Target area At a vertex position in the ECEF coordinate system, then from the satellite The vector to this vertex can be expressed as .

[0036] According to the obtained basis vectors, we can get the vector In satellite The expression in the local rectangular coordinate system can be expressed as in

[0037] Then, using the obtained rectangular coordinates , and obtain the target area The vertex position of the satellite The local earth coordinate system can be expressed as ,in and Denotes azimuth and elevation respectively. Specifically, the satellite The position of the satellite is taken as the origin of the satellite's local terrestrial coordinate system.

[0038] S103, in the satellite local surface coordinate system, fitting the shape of the target area according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain a fitted satellite beam projection profile; Among them, reasonable angular domain beam cell shape design can avoid beam deformation. Considering that the greater the distance between the ground and the satellite, the more serious the beam deformation, the cell projection in the satellite local spherical coordinate system tends to be flat. Therefore, an ellipse is used to fit the half-power beam width profile of the required beam cell shape mode.

[0039] In some embodiments, the specific process of fitting the shape of the target area according to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system includes: calculating the characteristic parameters of the ellipse corresponding to the target area according to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system; based on the binary search method and the characteristic parameters of the ellipse, designing a satellite beam projection profile to fit the shape of the target area, and obtaining a fitted satellite beam projection profile.

[0040] The characteristic parameters of the ellipse include the coordinates of the center point of the ellipse, the rotation angle and the semi-major axis.

[0041] Specifically, based on the binary search method and the characteristic parameters of the ellipse, a satellite beam projection profile is designed to fit the shape of the target area. The specific process of obtaining the fitted satellite beam projection profile includes: obtaining the minimum semi-minor axis of the ellipse through the binary search method according to the center point coordinates, the rotation angle and the semi-major axis; generating a half-power beam width profile of the beam area shape required for the target area according to the center point coordinates, the rotation angle, the semi-major axis and the minimum semi-minor axis; and using the half-power beam width profile of the beam area shape required for the target area as the fitted satellite beam projection profile.

[0042] Specifically, the designed shape also includes an elliptical transition area, which is used to fit the main lobe attenuation area, and the elliptical transition area is obtained by proportionally enlarging the fitted satellite beam projection profile; the method also includes: based on the satellite beam projection profile, generating a normalized beam gain pattern; wherein the normalized beam gain pattern includes a half-power beam width area corresponding to the satellite beam projection profile, a main lobe attenuation area corresponding to the elliptical transition area, and a side lobe area.

[0043] For example, the characteristic parameters of an ellipse are ,in is the center of the ellipse, is the rotation angle, and are the semi-major axis and the semi-minor axis respectively. Assume that the point On an ellipse, the equation of the ellipse can be expressed as:

[0044] in, and Respectively expressed as: ;as well as .

[0045] This application defines Target area The vertex coordinates are known. The specific algorithm process of converting the vertex position coordinates into the angular coordinates in the satellite local surface coordinate system can be used to obtain each vertex. The angular coordinates in the satellite's local surface coordinate system are expressed as , Then, the center of gravity of the cell projection is set as the center of the ellipse, and the calculation formula is: ; Semi-major axis Set to the maximum vertex spacing, the value is: ; The two vertices with the largest distance between them are respectively and The rotation angle It can be calculated as: ; To ensure that the required ellipse completely covers the cell projection, at the given center point , rotation angle and semi-major axis In the case of , the minimum semi-minor axis can be obtained by binary search method Based on the estimated ellipse parameters , we can get the half-power beam width profile of the desired beam cell shape , which can be expressed as:

[0046] Since the transition zone is very sharp, the Gibbs effect can cause a large error between the obtained satellite beam projection profile and the desired beam cell shape, making it impossible to guarantee the target transmission gain within the cell.

[0047] In order to smooth the negative impact of gain mutation, an elliptical transition region is added to the beam cell shape design. This transition region is denoted as , and its calculation formula is

[0048] in is a constant. Finally, the normalized beam gain pattern is: ; in and is the preset attenuation coefficient.

[0049] Inspired by the recent implementation of efficient 2D-IFFT beamforming on satellites, a non-iterative algorithm is used to quickly compute antenna element weights. Specifically, the proposed algorithm connects the beam cell shape design and the filter window design, which can utilize IFFT operations to accelerate the computation.

[0050] S104: Generate satellite antenna weights suitable for the target area based on the fitted satellite beam projection profile.

[0051] In some embodiments, based on the fitted satellite beam projection profile, the specific process of generating satellite antenna weights suitable for the target area includes: defining tap weights of a two-dimensional finite impulse response; applying Hermitian symmetry to the tap weights to symmetrically process the weight coefficients of the satellite's antenna array to obtain target tap weights; obtaining the tap weight amplitude response of the target tap weights; establishing a one-to-one mapping relationship from the tap weight amplitude response to the normalized beam gain pattern of the satellite beam projection profile, the mapping relationship being a one-to-one conversion of the azimuth and elevation angles in the normalized beam gain pattern to the antenna weights of the satellite phased array in the X-axis and Y-axis directions; and calculating the satellite antenna weights suitable for the target area based on the mapping relationship and a preset inverse fast Fourier transform algorithm. Hermitian symmetry can be used to simplify the calculation of Fourier transforms.

[0052] Specifically, we can assume and is an odd number, where and Phased array Axis and The number of antenna elements along the axis. Definition is the tap weight of the two-dimensional finite impulse response, and its amplitude response is expressed as ,in .

[0053] First, Hermitian symmetry is imposed on the tap weights, namely:

[0054] definition and .

[0055] Then, create To the normalized beam gain pattern The one-to-one mapping is expressed as: ;in ,and satisfy:

[0056] definition , and its IFFT result is expressed as Then, the normalized antenna element weights It can be calculated as:

[0057] in Represents the conjugate operation.

[0058] Then, the antenna element weights Calculated as: ; in is the antenna power.

[0059] In the embodiment of the present application, the direction and shape of the beam are controlled by adjusting the weights of the antenna array to optimize signal coverage and reduce interference. This method is particularly suitable for dynamic environments or scenarios that require rapid response, such as mobile satellite communications. This method can ensure that effective communication coverage of the target area is maintained even when the satellite moves or ground conditions change.

[0060] In order to obtain stable receiving power within a certain area and overcome inter-beam interference caused by satellite beam deformation, this application uses low-complexity regional projection fitting and non-iterative antenna weight calculation to quickly generate satellite beam shapes, solve the problem of the inability to quickly generate adaptive beam areas in existing solutions, and reduce the impact of the high dynamic characteristics of satellites. At the same time, through the designed coordinate transformation and beam area design, the interference caused by beam deformation is reduced. When applied to asynchronous satellite squint service scenarios, it is not easy to cause beam pattern deformation, which can reduce interference between cells and ensure stable service quality for users in the cell.

[0061] The following is an embodiment of the device of the present application, which can be used to execute the embodiment of the method of the present application. For details not disclosed in the embodiment of the device of the present application, please refer to the embodiment of the method of the present application.

[0062] See also Figure 3 , which shows a schematic diagram of the structure of a satellite antenna weight generation device provided by an exemplary embodiment of the present application. The satellite antenna weight generation device can be implemented as all or part of an electronic device through software, hardware or a combination of both. The device 1 includes an acquisition module 10, a conversion module 20, a fitting module 30, and a generation module 40.

[0063] An acquisition module 10 is used to acquire a set of boundary vertices of a target area in the earth in a preset earth-centered earth-fixed coordinate system; A conversion module 20, used for converting the vertex position coordinates of each boundary vertex in the boundary vertex set into an angular coordinate in the satellite local surface coordinate system; A fitting module 30 is used to fit the shape of the target area in the satellite local terrestrial coordinate system according to the angular coordinates of each boundary vertex in the satellite local terrestrial coordinate system to obtain a fitted satellite beam projection profile; The generating module 40 is used to generate satellite antenna weights suitable for the target area based on the fitted satellite beam projection profile.

[0064] It should be noted that the satellite antenna weight generation device provided in the above embodiment only uses the division of the above functional modules as an example when executing the satellite antenna weight generation method. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above. In addition, the satellite antenna weight generation device provided in the above embodiment and the satellite antenna weight generation method embodiment belong to the same concept, and the implementation process thereof is detailed in the method embodiment, which will not be repeated here.

[0065] The serial numbers of the above-mentioned embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0066] In order to obtain stable receiving power within a certain area and overcome inter-beam interference caused by satellite beam deformation, this application uses low-complexity regional projection fitting and non-iterative antenna weight calculation to quickly generate satellite beam shapes, solve the problem of the inability to quickly generate adaptive beam areas in existing solutions, and reduce the impact of the high dynamic characteristics of satellites. At the same time, through the designed coordinate transformation and beam area design, the interference caused by beam deformation is reduced. When applied to asynchronous satellite squint service scenarios, it is not easy to cause beam pattern deformation, which can reduce interference between cells and ensure stable service quality for users in the cell.

[0067] The present application also provides a computer-readable medium having program instructions stored thereon, and when the program instructions are executed by a processor, the satellite antenna weight generation method provided by the above-mentioned various method embodiments is implemented.

[0068] The present application also provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the satellite antenna weight generation method of each of the above method embodiments.

[0069] See also Figure 4 , is a schematic diagram of the structure of an electronic device provided in an embodiment of the present application. Figure 4As shown, the electronic device 1000 may include: at least one processor 1001 , at least one network interface 1004 , a user interface 1003 , a memory 1005 , and at least one communication bus 1002 .

[0070] The communication bus 1002 is used to realize the connection and communication between these components.

[0071] The user interface 1003 may include a display screen (Display) and a camera (Camera). Optionally, the user interface 1003 may also include a standard wired interface and a wireless interface.

[0072] The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-FI interface).

[0073] Among them, the processor 1001 may include one or more processing cores. The processor 1001 uses various interfaces and lines to connect various parts of the entire electronic device 1000, and executes various functions and processes data of the electronic device 1000 by running or executing instructions, programs, code sets or instruction sets stored in the memory 1005, and calling data stored in the memory 1005. Optionally, the processor 1001 can be implemented in at least one hardware form of digital signal processing (Digital Signal Processing, DSP), field programmable gate array (Field-Programmable Gate Array, FPGA), and programmable logic array (Programmable Logic Array, PLA). The processor 1001 can integrate one or a combination of a central processing unit (Central Processing Unit, CPU), a graphics processing unit (Graphics Processing Unit, GPU) and a modem. Among them, the CPU mainly processes operating devices, user interfaces and applications, etc.; the GPU is responsible for rendering and drawing the content to be displayed on the display screen; the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor 1001, and it can be implemented separately through a chip.

[0074] Among them, the memory 1005 may include a random access memory (Random Access Memory, RAM) and may also include a read-only memory (Read-Only Memory). Optionally, the memory 1005 includes a non-transitory computer-readable storage medium. The memory 1005 can be used to store instructions, programs, codes, code sets or instruction sets. The memory 1005 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing the operating device, instructions for at least one function (such as a touch function, a sound playback function, an image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc.; the data storage area may store data involved in the above-mentioned various method embodiments, etc. The memory 1005 may also be optionally at least one storage device located away from the aforementioned processor 1001. As Figure 4 As shown, the memory 1005 as a computer storage medium may include an operating device, a network communication module, a user interface module, and a satellite antenna weight generation application.

[0075] exist Figure 4 In the electronic device 1000 shown, the user interface 1003 is mainly used to provide an input interface for the user and obtain data input by the user; and the processor 1001 can be used to call the satellite antenna weight generation application stored in the memory 1005, and specifically perform the following operations: In a preset Earth-centered Earth-fixed coordinate system, a set of boundary vertices of a target area in the Earth is obtained; The vertex position coordinates of each boundary vertex in the boundary vertex set are converted into angular coordinates in the satellite local surface coordinate system; In the satellite local surface coordinate system, the shape of the target area is fitted according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain a fitted satellite beam projection profile; Based on the fitted satellite beam projection profile, satellite antenna weights suitable for the target area are generated.

[0076] In one embodiment, when the processor 1001 converts the vertex position coordinates into the angular coordinates in the satellite local surface coordinate system, the processor 1001 specifically performs the following operations: In a preset Earth-centered Earth-fixed coordinate system, obtaining satellite position coordinates and satellite velocity vector of the satellite; Calculate, according to the satellite velocity vector, a first unit vector of the satellite local rectangular coordinate system X-axis based on the satellite position coordinate and a second unit vector of the satellite local rectangular coordinate system Z-axis based on the satellite position coordinate; Calculate the vector product between the first unit vector and the second unit vector to obtain a third unit vector of the Y axis of the satellite local rectangular coordinate system based on the satellite position coordinates; Calculate rectangular coordinates according to the vertex position coordinates, the satellite position coordinates, the first unit vector, the second unit vector, and the third unit vector; Based on the rectangular coordinates, a coordinate representation of the vertex position coordinates in the satellite local terrestrial coordinate system is generated as the angular coordinates of each boundary vertex in the satellite local terrestrial coordinate system.

[0077] In one embodiment, when the processor 1001 performs fitting of the shape of the target area according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain the fitted satellite beam projection profile, the processor 1001 specifically performs the following operations: According to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system, the characteristic parameters of the ellipse corresponding to the target area are calculated; Based on the binary search method and the characteristic parameters of the ellipse, the satellite beam projection profile is designed to fit the shape of the target area, and the fitted satellite beam projection profile is obtained.

[0078] In one embodiment, when the processor 1001 executes the binary search method and the characteristic parameters of the ellipse to design the satellite beam projection profile to fit the shape of the target area and obtain the fitted satellite beam projection profile, the processor 1001 specifically performs the following operations: According to the center point coordinates, rotation angle and semi-major axis, the minimum semi-minor axis of the ellipse is obtained by binary search method; Generate a half-power beam width profile of a beam area shape required for a target area according to the center point coordinates, the rotation angle, the semi-major axis and the minimum semi-minor axis; The half-power beam width profile of the beam area shape required for the target area is used as the fitted satellite beam projection profile.

[0079] In one embodiment, the processor 1001 further performs the following operations: Based on the satellite beam projection profile, a normalized beam gain pattern is generated; wherein the normalized beam gain pattern includes a half-power beam width region corresponding to the satellite beam projection profile, a main lobe attenuation region corresponding to the elliptical transition region, and a side lobe region.

[0080] In one embodiment, when the processor 1001 generates satellite antenna weights applicable to the target area based on the fitted satellite beam projection profile, the processor 1001 specifically performs the following operations: Define the tap weights of a two-dimensional finite impulse response; Applying Hermitian symmetry to the tap weights to symmetrically process the weight coefficients of the satellite's antenna array to obtain target tap weights; obtaining a tap weight magnitude response of a target tap weight; Establishing a one-to-one mapping relationship between the tap weight amplitude response and the normalized beam gain pattern of the satellite beam projection profile, the mapping relationship being a one-to-one conversion between the azimuth angle and the elevation angle in the normalized beam gain pattern and the antenna weights of the satellite phased array in the X-axis and Y-axis directions; Based on the mapping relationship and a preset inverse fast Fourier transform algorithm, the satellite antenna weights suitable for the target area are calculated.

[0081] In order to obtain stable receiving power within a certain area and overcome inter-beam interference caused by satellite beam deformation, this application uses low-complexity regional projection fitting and non-iterative antenna weight calculation to quickly generate satellite beam shapes, solve the problem of the inability to quickly generate adaptive beam areas in existing solutions, and reduce the impact of the high dynamic characteristics of satellites. At the same time, through the designed coordinate transformation and beam area design, the interference caused by beam deformation is reduced. When applied to asynchronous satellite squint service scenarios, it is not easy to cause beam pattern deformation, which can reduce interference between cells and ensure stable service quality for users in the cell.

[0082] A person skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be implemented by instructing related hardware through a computer program, and the program for generating the satellite antenna weights can be stored in a computer-readable storage medium, and when the program is executed, it can include the processes of the embodiments of the above-mentioned methods. The storage medium of the program for generating the satellite antenna weights can be a magnetic disk, an optical disk, a read-only storage memory, or a random access memory, etc.

[0083] The above disclosure is only the preferred embodiment of the present application, which certainly cannot be used to limit the scope of rights of the present application. Therefore, equivalent changes made according to the claims of the present application are still within the scope covered by the present application.

Claims

1. A method for generating antenna weights of a satellite, characterized in that: The method comprises: In a preset Earth-centered Earth-fixed coordinate system, a set of boundary vertices of a target area in the Earth is obtained; Converting the vertex position coordinates of each boundary vertex in the boundary vertex set into angular coordinates in the satellite local surface coordinate system; In the satellite local surface coordinate system, the shape of the target area is fitted according to the angular coordinates of each boundary vertex in the satellite local surface coordinate system to obtain a fitted satellite beam projection profile; Based on the fitted satellite beam projection profile, satellite antenna weights suitable for the target area are generated.

2. The method according to claim 1, characterized in that Converting the vertex position coordinates into angular coordinates in the satellite's local surface coordinate system includes: In a preset Earth-centered Earth-fixed coordinate system, obtaining satellite position coordinates and satellite velocity vector of the satellite; Calculate, according to the satellite velocity vector, a first unit vector of the satellite local rectangular coordinate system X-axis based on the satellite position coordinate and a second unit vector of the satellite local rectangular coordinate system Z-axis based on the satellite position coordinate; Calculate the vector product between the first unit vector and the second unit vector to obtain a third unit vector of the Y axis of the satellite local rectangular coordinate system based on the satellite position coordinates; Calculate rectangular coordinates according to the vertex position coordinates, the satellite position coordinates, the first unit vector, the second unit vector, and the third unit vector; Based on the rectangular coordinates, a coordinate representation of the vertex position coordinates in the satellite local terrestrial coordinate system is generated as the angular coordinates of each boundary vertex in the satellite local terrestrial coordinate system.

3. The method according to claim 2, characterized in that The directions of the X-axis and the Z-axis are set according to the direction of movement of the satellite and the direction from the satellite to the center of the earth, respectively. The direction of the Y-axis is determined by the right-hand rule. The origin of the satellite's local surface coordinate system is the satellite position coordinate. The coordinate representation includes a target vector calculated based on the rectangular coordinates and an azimuth and elevation of the vertex position coordinate relative to the satellite position coordinate.

4. The method according to claim 1, characterized in that: The step of fitting the shape of the target area according to the angular coordinates of each boundary vertex in the satellite's local surface coordinate system to obtain a fitted satellite beam projection profile includes: Calculating characteristic parameters of the ellipse corresponding to the target area according to the angular coordinates of each boundary vertex in the satellite's local terrestrial coordinate system; Based on the binary search method and the characteristic parameters of the ellipse, a satellite beam projection profile is designed to fit the shape of the target area, thereby obtaining a fitted satellite beam projection profile.

5. The method according to claim 4, characterized in that The characteristic parameters of the ellipse include the coordinates of the center point of the ellipse, the rotation angle and the semi-major axis; The method of designing a satellite beam projection profile to fit the shape of the target area based on the binary search method and the characteristic parameters of the ellipse to obtain a fitted satellite beam projection profile includes: According to the center point coordinates, the rotation angle and the semi-major axis, the minimum semi-minor axis of the ellipse is obtained by a binary search method; Generate a half-power beam width profile of a beam area shape required for the target area according to the center point coordinates, the rotation angle, the semi-major axis and the minimum semi-minor axis; The half-power beam width profile of the beam area shape required for the target area is used as the fitted satellite beam projection profile.

6. The method according to claim 5, characterized in that The designed shape also includes an elliptical transition region, which is used to fit the main lobe attenuation region, and the elliptical transition region is obtained by proportionally enlarging the fitted satellite beam projection profile; The method further comprises: Based on the satellite beam projection profile, a normalized beam gain pattern is generated; wherein the normalized beam gain pattern includes a half-power beam width area corresponding to the satellite beam projection profile, a main lobe attenuation area and a side lobe area corresponding to the elliptical transition area.

7. The method according to claim 6, characterized in that The step of generating satellite antenna weights suitable for the target area based on the fitted satellite beam projection profile comprises: Define the tap weights of a two-dimensional finite impulse response; Applying Hermitian symmetry to the tap weights to perform symmetric processing on weight coefficients of the satellite antenna array to obtain target tap weights; Obtaining a tap weight amplitude response of the target tap weight; Establishing a one-to-one mapping relationship between the tap weight amplitude response and the normalized beam gain pattern of the satellite beam projection profile, wherein the mapping relationship is a one-to-one conversion between the azimuth angle and the elevation angle in the normalized beam gain pattern and the antenna weights of the satellite phased array in the X-axis and Y-axis directions; Based on the mapping relationship and a preset inverse fast Fourier transform algorithm, satellite antenna weights suitable for the target area are calculated.

8. A satellite antenna weight generation device, characterized in that: The device comprises: An acquisition module, used to acquire a set of boundary vertices of a target area in the earth in a preset earth-centered earth-fixed coordinate system; A conversion module, used for converting the vertex position coordinates of each boundary vertex in the boundary vertex set into angular coordinates in the satellite local surface coordinate system; A fitting module, used for fitting the shape of the target area in the satellite local terrestrial coordinate system according to the angular coordinates of each boundary vertex in the satellite local terrestrial coordinate system to obtain a fitted satellite beam projection profile; The generating module is used to generate satellite antenna weights suitable for the target area based on the fitted satellite beam projection profile.

9. A computer storage medium, characterized in that: The computer storage medium stores a plurality of instructions, and the instructions are suitable for being loaded by a processor and executing the method according to any one of claims 1 to 7.

10. An electronic device, characterized in that: include: A processor and a memory; wherein the memory stores a computer program, and the computer program is suitable for being loaded by the processor and executing the method according to any one of claims 1 to 7.

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