Single-satellite multi-ship hybrid beam crosstalk modeling method and device based on sea surface user area distribution

Abstract

The application provides a single-satellite multi-ship hybrid beam crosstalk modeling method and device based on a sea surface user area distribution, which comprises the following steps: performing beam geographic projection calculation based on satellite orbit ephemeris data and antenna pointing parameters to obtain a coverage boundary range and a beam center axis direction; performing analysis based on the coverage boundary range and ship historical trajectory points to obtain a main shaft direction angle, a centroid coordinate and a dispersion span; performing profile cutting on a satellite antenna far-field directional diagram based on the beam center axis direction and the main shaft direction angle to obtain a gain variation curve; performing interval mapping based on the centroid coordinate, the dispersion span and the gain variation curve to obtain a target gain distribution interval; performing energy integration based on the target gain distribution interval and the gain variation curve to obtain an equivalent interference coupling gain; and performing gain inversion based on the equivalent interference coupling gain and an expected signal coupling gain to obtain a hybrid beam crosstalk modeling result. The application improves the accuracy of the hybrid beam crosstalk modeling.

Description

Technical Field

[0001] This invention relates to the field of satellite communication technology, and in particular to a method and apparatus for modeling crosstalk between a single satellite and multiple ships using hybrid beams based on the distribution of user areas on the sea surface. Background Technology

[0002] In single-satellite multi-beam satellite communication systems, an accurate crosstalk model is needed to assess co-channel interference caused by frequency reuse. Existing crosstalk modeling methods typically assume that surface ship users are uniformly or isotropically randomly distributed within the beam coverage area, and calculate the interference gain based on this assumption using two-dimensional integration or point-by-point accumulation.

[0003] However, in reality, the spatial distribution of ships at sea is significantly non-uniform and directional (i.e., anisotropic) due to the influence of channel alignment, port location, and navigation rules. For example, they may cluster in narrow strips along specific channels. This neglect of the directional characteristics of the spatial distribution of users at sea means that existing methods, when using simplified uniform distribution models, cannot accurately reflect the extreme interference situations that occur when the main axis of user aggregation coincides with the high-gain region of the antenna sidelobes. On the other hand, using high-precision point-by-point simulation methods faces enormous computational burdens, making it difficult to meet the timeliness requirements of modeling in engineering applications. Therefore, existing methods fail to adaptively couple the geometric characteristics of user distribution (such as aggregation direction and dispersion) with the physical characteristics of the antenna pattern, making the calculated gain unable to truly reflect the interference level under non-uniform distribution, thus reducing the accuracy of single-satellite multi-ship mixed beam crosstalk modeling. Summary of the Invention

[0004] This invention provides a method and apparatus for modeling crosstalk between a single satellite and multiple ships using hybrid beams based on the distribution of user areas on the sea surface, aiming to improve the accuracy of modeling crosstalk between a single satellite and multiple ships using hybrid beams.

[0005] In a first aspect, the present invention provides a method for modeling crosstalk between a single satellite and multiple ships using hybrid beams based on the distribution of user areas on the sea surface, including: Based on satellite orbit ephemeris data and antenna pointing parameters, beam geographic projection calculation is performed to obtain the coverage boundary range and beam center axis orientation of each beam. Based on each coverage boundary range and ship historical trajectory points, analysis is performed to obtain the main axis direction angle, centroid coordinates and dispersion span of user distribution. Based on the azimuth of the beam center axis and the direction angle of the main axis, the far-field radiation pattern of the satellite antenna is profiled to obtain the gain variation curve along the main axis direction. Based on the centroid coordinates, the dispersion span and the gain variation curve, interval mapping is performed to obtain the target gain distribution interval of the equivalent interference source. Based on the target gain distribution range and gain change curve, energy integration is performed to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam. Gain inversion is performed based on the equivalent interference coupling gain and the desired signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

[0006] In a second aspect, the present invention also provides a single-satellite multi-ship hybrid beam crosstalk modeling device based on sea surface user area distribution, for implementing the single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution as described in the first aspect; the device includes: The user distribution analysis module is used to perform beam geographic projection calculation based on satellite orbit ephemeris data and antenna pointing parameters to obtain the coverage boundary range and beam center axis orientation of each beam. Based on each coverage boundary range and ship historical trajectory points, the module analyzes to obtain the principal axis direction angle, centroid coordinates and dispersion span of the user distribution. The gain interval mapping module is used to cross-section the far-field radiation pattern of the satellite antenna based on the azimuth of the beam center axis and the direction angle of the main axis, to obtain the gain variation curve along the main axis direction, and to perform interval mapping based on the centroid coordinates, the dispersion span and the gain variation curve to obtain the target gain distribution interval of the equivalent interference source. The interference gain coupling module is used to perform energy integration based on the target gain distribution range and gain change curve to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam. The gain inversion module is used to perform gain inversion based on the equivalent interference coupling gain and the expected signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

[0007] Thirdly, the present invention also provides an electronic device, comprising: a memory for storing a computer program; and a processor for reading and executing the computer program, thereby realizing the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface as described above.

[0008] Fourthly, the present invention also provides a non-transitory computer-readable storage medium storing a computer program, which, when executed by a processor, implements the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface as described above.

[0009] Fifthly, the present invention also provides a computer program product, including a computer program that, when executed by a processor, implements the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface as described above.

[0010] The single-satellite multi-ship hybrid beam crosstalk modeling method provided in this invention provides a method for modeling crosstalk between multiple ships based on the distribution of users on the sea surface. This method uses beam geographic projection to calculate the coverage boundary range of each beam, the azimuth of the beam's central axis, and the principal axis direction angle, centroid coordinates, and dispersion span of the sea surface user distribution. It accurately captures the non-uniform, anisotropic spatial distribution geometry of sea surface ship users influenced by waterways, ports, and navigation rules. Based on beam physical parameters and user distribution characteristic parameters, it obtains a gain variation curve that fits the user aggregation direction by performing a principal axis direction profile on the satellite antenna far-field radiation pattern. Combined with the user centroid coordinates and dispersion span, it completes interval mapping to obtain the target gain distribution interval of the equivalent interference source. Adaptive coupling between the physical characteristics of the antenna pattern and the non-uniform geometric features of the user distribution is achieved. Energy integration is performed based on the gain variation curve and the target gain distribution range to accurately solve the equivalent interference coupling gain of a single interfering beam to the interfered beam. This realistically recreates the extreme interference scenario when the user's main focus axis coincides with the high gain region of the antenna sidelobe, avoiding the problem that uniform distribution models cannot reflect real extreme interference. Based on the final solved equivalent interference coupling gain and the expected signal coupling gain of the interfered beam, gain inversion is completed, resulting in a single-satellite multi-ship hybrid beam crosstalk modeling result that takes into account both the non-uniform user focus effect and the modeling timeliness, thus improving the accuracy of single-satellite multi-ship hybrid beam crosstalk modeling. Attached Figure Description

[0011] Figure 1 This is a flowchart illustrating the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface provided in this embodiment of the invention. Figure 2 This is a schematic diagram of the structure of the single-satellite multi-ship hybrid beam crosstalk modeling device based on the distribution of user areas on the sea surface provided in an embodiment of the present invention; Figure 3 An embodiment diagram of the electronic device provided in this invention; Figure 4 An embodiment diagram of a computer-readable storage medium provided in accordance with the present invention. Detailed Implementation

[0012] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0013] In the description of this invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0014] In the description of this invention, the term "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this invention is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use the invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the invention can be made without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the invention with unnecessary detail. Therefore, the invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed herein.

[0015] Optionally, see Figure 1 , Figure 1 This is a flowchart illustrating the single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution provided by the present invention. In this embodiment of the invention, the executing entity of the single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution is a ship management device. Therefore, the single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution includes: Step 10: Perform beam geoprojection calculation based on satellite orbit ephemeris data and antenna pointing parameters to obtain the coverage boundary range and beam center axis orientation of each beam. Analyze each coverage boundary range and historical ship trajectory points to obtain the principal axis direction angle, centroid coordinates, and dispersion span of user distribution.

[0016] Optionally, the ship management device extracts the satellite's three-dimensional spatial position coordinates at the current moment from the satellite orbital ephemeris data. These coordinates include the satellite's longitude, latitude, and orbital altitude. It also extracts the beam deflection angle and beam azimuth angle for each beam from the phased array antenna pointing parameters. The beam deflection angle is the angle by which the beam deviates from the antenna normal direction, determined by the feed phase difference of each element in the phased array antenna. The beam azimuth angle is the angle between the projection of the beam deviation direction onto the phased array antenna aperture plane and the reference axis of the aperture plane. For each beam, the ship management device uses the satellite's three-dimensional spatial position coordinates as the ray starting point, determines the spatial pointing direction of the beam's central axis using the beam deflection angle and beam azimuth angle, and intersects the Earth's ellipsoid along this spatial pointing direction. The intersection point of the ray and the Earth's ellipsoid is then used as the ground projection point of the beam center. Using the ground projection point of the beam center as the center and the ground projection radius corresponding to the half-power beamwidth of the phased array antenna as the distance parameter, a closed area is delineated on the Earth's ellipsoid. This closed area is taken as the coverage boundary of the beam. The angle between the projection of the spatial pointing direction of the beam center axis on the horizontal plane and the due north direction is recorded as the azimuth of the beam center axis.

[0017] The ship management device acquires historical ship trajectory points, which are collections of ship position records located within the coverage area of ​​each beam, acquired by the Automatic Identification System (AIS) within a preset statistical time window. Each ship position record includes the ship's longitude and latitude coordinates. For each beam's coverage boundary, all ship position records falling within that boundary are selected from the historical trajectory points to form the beam-specific trajectory points.

[0018] The ship management device performs principal component analysis on the trajectory points within the beam. Specifically, it subtracts the corresponding mean longitude and mean latitude coordinates from the ship longitude and latitude coordinates of all ship position records within the beam to obtain a decentralized coordinate matrix. It then calculates the covariance matrix of the decentralized coordinate matrix and performs eigenvalue decomposition on the covariance matrix to obtain a first eigenvalue and a first eigenvector. The first eigenvalue is the largest eigenvalue of the covariance matrix, and the first eigenvector is the eigenvector corresponding to the first eigenvalue. The angle between the projection direction of the first eigenvector onto the horizontal plane and the due north direction is recorded as the principal axis direction angle, which represents the extension direction of the ship positions within the beam trajectory points along the direction of maximum dispersion. The arithmetic mean of the longitude coordinates of all ships within the beam trajectory points is used as the centroid longitude coordinate, and the arithmetic mean of the latitude coordinates of all ships is used as the centroid latitude coordinate. The centroid coordinate is composed of the centroid longitude and centroid latitude coordinates, representing the spatial center of concentration of ship distribution within the beam trajectory points. The difference between the maximum and minimum values ​​of the projection values ​​of each ship position record in the trajectory points within the beam onto the direction corresponding to the main axis direction angle is recorded as the main axis span. The difference between the maximum and minimum values ​​of the projection values ​​of each ship position record onto the direction perpendicular to the main axis direction angle is recorded as the secondary axis span. The ratio of the main axis span to the secondary axis span is recorded as the dispersion span. The dispersion span characterizes the degree of anisotropy of the ship distribution in the trajectory points within the beam. When the dispersion span is greater than 1, it indicates that the ship distribution exhibits directional clustering characteristics.

[0019] For example, suppose satellite orbital ephemeris data indicates that the satellite is currently located at 110°E, 0°N, and at an orbital altitude of 35,786 km. The phased array antenna has 7 beams. Taking the first beam as an example, its phased array antenna pointing parameters include a beam deflection angle of 8°, a beam azimuth angle of 45°, and a half-power beamwidth of 3°. Using the satellite position (110°E, 0°N, 35,786 km) as the ray origin, and using the beam deflection angle of 8° and the beam azimuth angle of 45° to determine the spatial pointing direction of the first beam's central axis, a ray is drawn along this direction and intersected with the Earth's ellipsoid (using the WGS-84 ellipsoid model). The ground projection point of the first beam's center is found to be located at 112.5°E, 2.1°N. Using the ground projection point of the first beam center as the center, and calculating the ground projection radius as 93 kilometers based on the half-power beamwidth of 3° and the satellite orbital altitude of 35,786 kilometers, a circular closed region with a radius of 93 kilometers is delineated on the Earth's ellipsoid. This circular closed region serves as the coverage boundary of the first beam. The angle between the projection of the spatial pointing direction of the first beam center axis onto the horizontal plane and the due north direction is 45°, meaning the azimuth of the first beam center axis is 45°.

[0020] Assuming that, after principal component analysis, the first beam has a principal axis direction angle of 30°, a centroid coordinate of (112.52°, 2.15°), a maximum projection value of 5.2 km and a minimum of -4.8 km in the direction corresponding to the 30° principal axis direction angle, and a principal axis span of 10 km; and a maximum projection value of 1.4 km and a minimum of -1.6 km in the direction perpendicular to 30°, with a secondary axis span of 3 km; and a dispersion span of 3. The second beam uses the same frequency as the first beam. The ground projection point of the second beam's beam center is located at 113.8°E, 3.5°N, covering a circular area with a radius of 93 km. The beam center axis azimuth is 30°. The subset of trajectory points within the second beam contains 72 ship position records, with a principal axis direction angle of 25°, a centroid coordinate of (113.82°, 3.53°), and a dispersion span of 4.

[0021] Step 20: Based on the azimuth of the beam center axis and the direction angle of the main axis, the far-field radiation pattern of the satellite antenna is profiled to obtain the gain variation curve along the main axis direction. Based on the centroid coordinates, scattering span and gain variation curve, interval mapping is performed to obtain the target gain distribution interval of the equivalent interference source.

[0022] Optionally, the satellite antenna far-field pattern refers to a two-dimensional gain distribution data table with the angle of deviation from the beam center axis as the independent variable and the antenna radiation gain as the dependent variable. It is obtained by pre-calibrating the element arrangement, element spacing, and feed amplitude and phase of each element in the phased array antenna, characterizing the radiation characteristics of the satellite antenna at different electronic scanning angles. The ship management device uses the difference between the azimuth of the interfering beam's beam center axis and the angle of the interfering beam's principal axis as the profile intercept angle. It extracts the gain variation curve along the direction of this profile intercept angle in the satellite antenna far-field pattern, obtaining the gain variation curve along the principal axis direction, as described in steps 201 to 204. The gain variation curve refers to the curve in the satellite antenna far-field pattern where the gain value continuously changes with the angle of deviation from the beam center axis, intercepted along a specific profile direction.

[0023] Optionally, the equivalent interference source refers to all ship users in a non-uniformly distributed area covered by the interference beam as equivalent interference sources. The antenna gain of the interference source is determined by the gain value corresponding to its location on the far-field radiation pattern of the satellite antenna. The ship management device maps the angular range occupied by the equivalent interference source onto the gain variation curve based on the offset distance of the centroid coordinates of the interference beam relative to the ground projection point of the interference beam center, combined with the principal axis span corresponding to the dispersion span, to obtain the target gain distribution range, as detailed in steps 205 to 208. The target gain distribution range refers to the deviation angular range corresponding to the equivalent interference source on the gain variation curve, determined by the projection of the centroid position and dispersion range of the ships within the interference beam coverage area onto the gain variation curve.

[0024] Step 30: Perform energy integration based on the target gain distribution range and gain change curve to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam.

[0025] Optionally, the ship management device extracts the start angle and end angle of the interval from the target gain distribution interval of the interfering beam. On the gain change curve, with the start angle as the lower limit of integration and the end angle as the upper limit of integration, it performs energy integration on the gain value of the gain change curve within the interval. The energy integration process is as follows: the angle range between the start angle and the end angle of the interval is divided into multiple sub-intervals at equal intervals according to a preset angle step. For each sub-interval, the gain value corresponding to the midpoint angle of the gain change curve in the sub-interval is read. The gain value is converted from a decibel value to a linear gain value. The linear gain value is multiplied by the preset angle step to obtain the area micro-element of the sub-interval. The area micro-element of all sub-intervals is summed to obtain the total linear integral. The total linear integral is converted to a decibel value. This decibel value is used as the equivalent interference coupling gain generated by a single interfering beam on the interfering beam.

[0026] In energy integration calculation, the gain value of the gain variation curve within the target gain distribution interval reflects the radiation gain level of the satellite antenna at the location of the ship user within the interference beam coverage area. Energy integration calculation involves spatially accumulating and aggregating the interference signal energy received by a non-uniformly distributed group of ship users at various locations within the interference beam coverage area according to the density weight of the ship distribution, thereby obtaining an equivalent gain value representing the overall interference intensity. When the main axis of the ship distribution coincides with the high-gain sidelobe region in the gain variation curve, the target gain distribution interval falls into the angle segment with higher sidelobe gain in the gain variation curve, resulting in a larger energy integration result and a correspondingly higher equivalent interference coupling gain. Conversely, when the main axis of the ship distribution deviates from the high-gain sidelobe region, the target gain distribution interval falls into the angle segment with lower sidelobe gain in the gain variation curve, resulting in a smaller energy integration result and a correspondingly lower equivalent interference coupling gain.

[0027] For example, taking the first beam as the interfering beam and the second beam as the interfered beam, both beams use the same frequency. Assume that the target gain distribution range of the first beam mapped on the gain variation curve is from an deviation angle of -6° to +6°. Extracting the starting angle of the interval from the target gain distribution range of the first beam as -6° and the ending angle as +6°, the 12° angle range between -6° and +6° is divided into 12 sub-intervals at preset angle steps of 1°. For each sub-interval, read the gain value corresponding to the midpoint angle of the gain change curve at that sub-interval. Assuming the midpoint angles of the 12 sub-intervals are -5.5°, -4.5°, -3.5°, -2.5°, -1.5°, -0.5°, 0.5°, 1.5°, 2.5°, 3.5°, 4.5°, and 5.5° respectively, the corresponding gain values ​​are -18, -15, -12, -9, -6, -3, -3, -6, -9, -12, -15, and -18 dB respectively.

[0028] The 12 gain values ​​were converted from decibels to linear gain values. The conversion process involved exponentiation of the gain value by 10, resulting in 12 linear gain values ​​of 0.0158, 0.0316, 0.0631, 0.1259, 0.2512, 0.5012, 0.5012, 0.2512, 0.1259, 0.0631, 0.0316, and 0.0158. Each linear gain value was multiplied by a preset angle step of 1 to obtain 12 area micro-elements, which were 0.0158, 0.0316, 0.0631, 0.1259, 0.2512, 0.5012, 0.5012, 0.2512, 0.1259, 0.0631, 0.0316, and 0.0158. Summing all 12 area elements yields a total linear integral of 1.9776.

[0029] The total linear integral of 1.9776 is converted to a decibel value by taking the logarithm of the base 10 and then multiplying by 10, resulting in an equivalent interference coupling gain of 2.96 dB, which is rounded to 3 dB.

[0030] Following the same processing procedure as the first beam for the second beam, energy integration is performed on the remaining interfering beams using the same frequency to obtain the equivalent interference coupling gain of each interfering beam to the interfered beam.

[0031] Step 40: Perform gain inversion based on the equivalent interference coupling gain and the desired signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

[0032] Optionally, the desired signal coupling gain refers to the antenna gain value corresponding to the location of the ship user within the coverage area of ​​the interfered beam on the far-field pattern of the satellite antenna, reflecting the desired signal reception capability of the interfered beam for the ship user within its coverage area. Therefore, the ship management device uses the gain value corresponding to the centroid coordinates of the user distribution within the coverage area of ​​the interfered beam on the far-field pattern of the satellite antenna as the desired signal coupling gain of the interfered beam. The equivalent interference coupling gains corresponding to all interfering beams are summed in the linear domain to obtain the total interference gain. Based on the total interference gain and the desired signal coupling gain, the hybrid beam crosstalk modeling result for a single satellite with multiple ships is determined, as detailed in steps 401 to 404. The hybrid beam crosstalk modeling result refers to the relative interference level obtained after quantifying and estimating the co-channel interference level caused by frequency reuse among multiple beams on a single satellite under the condition of considering the non-uniform aggregation effect of sea surface users. It is used to evaluate the degree of inter-beam interference in a multi-beam satellite communication system.

[0033] The embodiments of the present invention improve the accuracy of single-satellite multi-ship hybrid beam crosstalk modeling.

[0034] Optionally, the processes of steps 201 to 204 include: Step 201: Based on the matching of the azimuth angle of the beam center axis and the direction angle of the main axis in the satellite attitude pointing table, the attitude deflection of the satellite antenna body coordinate system relative to the geographic coordinate system at the current moment is obtained, and the main lobe peak elevation angle of the beam center axis in the antenna body coordinate system is analyzed based on the antenna main lobe pointing table to obtain the main lobe reference.

[0035] Optionally, the ship management device acquires a satellite attitude pointing table and an antenna main lobe pointing table. The satellite attitude pointing table records the three-axis attitude angle data of the satellite at different times. The three-axis attitude angle data includes roll angle, pitch angle and yaw angle. The antenna main lobe pointing table records the mapping relationship between the beam deflection angle and beam azimuth angle of each beam in the phased array antenna and the pitch angle and azimuth angle in the antenna body coordinate system.

[0036] The ship management device matches the current time with the timestamp in the satellite attitude pointing table, extracts the roll angle, pitch angle and yaw angle corresponding to the current time, and uses the extracted roll angle, pitch angle and yaw angle as the attitude deflection of the satellite antenna body coordinate system relative to the geographic coordinate system at the current time.

[0037] The ship management device looks up the elevation angle in the antenna body coordinate system corresponding to the beam deflection angle and beam azimuth angle of the current beam in the antenna main lobe pointing table, takes the elevation angle as the main lobe peak elevation angle, and takes the main lobe peak elevation angle as the main lobe reference. The main lobe reference represents the elevation angle reference value where the current beam radiates the most concentrated energy in the antenna body coordinate system.

[0038] For example, assuming the current time is 12:00:00 on June 29, 2025, obtain the satellite attitude pointing table, match the current time with the timestamp in the satellite attitude pointing table, and extract the roll angle of 2°, elevation angle of -1°, and yaw angle of 3° corresponding to the current time. Use the roll angle of 2°, elevation angle of -1°, and yaw angle of 3° as the attitude deflection of the satellite antenna body coordinate system relative to the geographic coordinate system at the current time. Taking the first beam as an example, the beam deflection angle of the first beam is 8°, and the beam azimuth angle is 45°. Obtain the antenna main lobe pointing table, find the elevation angle of 10° in the antenna body coordinate system corresponding to the beam deflection angle of 8° and the beam azimuth angle of 45°, and use the elevation angle of 10° as the main lobe peak elevation angle of the first beam, and use the main lobe peak elevation angle of 10° as the main lobe reference of the first beam.

[0039] Step 202: Based on the attitude deflection, the principal axis orientation angle in geographic space is mapped to the antenna body coordinate system to obtain the target profile orientation.

[0040] Optionally, the ship management device constructs a three-dimensional spatial rotation matrix determined by the roll angle, pitch angle, and yaw angle in the attitude deflection. A unit direction vector is constructed in the geographic coordinate system, with its horizontal projection direction aligned with the principal axis direction angle and pointing towards the satellite's spatial location. The ship management device performs matrix multiplication on the unit direction vector and the three-dimensional spatial rotation matrix to obtain a mapping vector. The angle between the projection line of the mapping vector onto the horizontal projection plane of the antenna body coordinate system and the reference axis of the antenna body coordinate system is calculated. This angle is used as the target profile azimuth, which characterizes the azimuth angle of the ship's convergence principal axis direction in the antenna body coordinate system.

[0041] For example, a three-dimensional spatial rotation matrix is ​​constructed, defined by a roll angle of 2°, a pitch angle of -1°, and a yaw angle of 3°. Taking the first beam as an example, the principal axis direction angle of the first beam is 30°. A unit direction vector is constructed in the geographic coordinate system. The horizontal projection direction of the unit direction vector is consistent with the principal axis direction angle of 30° and points to the spatial position of the satellite. The unit direction vector is multiplied by the three-dimensional spatial rotation matrix to obtain the mapping vector. The angle between the projection line of the mapping vector on the horizontal projection plane of the antenna body coordinate system and the reference axis of the antenna body coordinate system is calculated to be 33°, which is the target profile azimuth of the first beam.

[0042] Step 203: Determine the dual-slice gain based on the gain corresponding to the elevation angle of two adjacent azimuth slices in the far-field radiation pattern of the satellite antenna for the target profile azimuth.

[0043] Optionally, the ship management device acquires a far-field radiation pattern of a satellite antenna, which consists of multiple azimuth slices. Each azimuth slice records a discrete data sequence of gain variation with elevation angle at a specific azimuth angle. Among the multiple azimuth slices in the far-field radiation pattern, the first azimuth slice with the closest azimuth angle value and less than the target profile azimuth, and the second azimuth slice with the closest azimuth angle value and greater than the target profile azimuth, are identified. The first and second azimuth slices are adjacent in azimuth angle value. The ship management device extracts a first gain value sequence corresponding to each elevation angle in the first azimuth slice and a second gain value sequence corresponding to each elevation angle in the second azimuth slice. The first and second gain value sequences are used as a dual-slice gain, which is a set of discrete antenna radiation gain data obtained from adjacent azimuth angle sections on both sides of the target profile azimuth.

[0044] For example, the far-field pattern of a satellite antenna contains multiple azimuth slices spaced 1° apart. Taking the first beam as an example, the target profile azimuth of the first beam is 33.5°. Among the multiple azimuth slices in the far-field pattern of the satellite antenna, the first azimuth slice with the closest azimuth value and less than the target profile azimuth of 33.5° is found, resulting in the first azimuth slice with an azimuth of 33°. The second azimuth slice with the closest azimuth value and greater than the target profile azimuth of 33.5° is found, resulting in the second azimuth slice with an azimuth of 34°. The first gain value sequence corresponding to each elevation angle in the first azimuth slice with an azimuth of 33° is extracted, and the second gain value sequence corresponding to each elevation angle in the second azimuth slice with an azimuth of 34° is extracted. The first gain value sequence and the second gain value sequence are used as the dual-slice gain of the first beam.

[0045] Step 204: Perform gain analysis based on the main lobe reference and dual-slice gain to obtain the gain variation curve.

[0046] Optionally, the ship management device performs gain analysis based on the main lobe reference and dual-slice gain to obtain the gain change curve, as described in steps 2041 to 2044.

[0047] This invention adaptively couples the geometric features of the distribution of ships on the sea surface with the physical characteristics of the antenna pattern, so that the final obtained gain variation curve can truly reflect the actual radiation gain distribution when the main axis of the ship's convergence coincides with or deviates from the high gain region of the antenna sidelobe under non-uniform distribution. This provides high-fidelity data support for subsequent accurate calculation of equivalent interference coupling gain and improves the accuracy of single-satellite multi-ship mixed beam crosstalk modeling.

[0048] Optionally, the process of steps 2041 to 2044 includes: Step 2041: Based on the azimuth difference between the target profile azimuth and two adjacent azimuth slices, determine the relative position ratio of the target profile azimuth between two adjacent azimuth slices.

[0049] Optionally, the ship management device subtracts the azimuth value of the first azimuth slice from the target profile azimuth value to obtain a first azimuth difference value, subtracts the target profile azimuth value from the azimuth value of the second azimuth slice to obtain a second azimuth difference value, and subtracts the azimuth value of the first azimuth slice from the azimuth value of the second azimuth slice to obtain a total azimuth difference value. The ship management device divides the first azimuth difference value by the total azimuth difference value, and uses the quotient as the relative position ratio of the target profile azimuth between two adjacent azimuth slices. This relative position ratio characterizes the spatial proximity of the target profile azimuth relative to the first and second azimuth slices in the azimuth dimension. For example, taking the first beam as an example, the target profile azimuth of the first beam is 33.5°, the azimuth of the first azimuth slice is 33°, and the azimuth of the second azimuth slice is 34°. Subtracting the azimuth of the first azimuth slice from the target profile azimuth of 33.5° yields a first azimuth difference value of 0.5. Subtracting the target profile azimuth 33.5 from the azimuth angle 34 of the second azimuth slice yields a second azimuth difference of 0.5. Subtracting the azimuth angle 33 of the first azimuth slice from the azimuth angle 34 of the second azimuth slice yields a total azimuth difference of 1. Dividing the first azimuth difference of 0.5 by the total azimuth difference of 1 yields a relative position ratio of 0.5 between the target profile azimuth of the first beam and two adjacent azimuth slices.

[0050] Step 2042: Based on the dual-slice gain and the relative position ratio, the gains corresponding to the same pitch angle in the two azimuth slices are linearly combined to generate a gain sequence along the main axis direction of the target profile azimuth.

[0051] Optionally, the ship management device subtracts the relative position ratio from the numerical value 1 to obtain a first weighting coefficient, and uses the relative position ratio as a second weighting coefficient. For each identical pitch angle node contained in the first and second gain value sequences in the dual-slice gain, the first gain value corresponding to that pitch angle node in the first gain value sequence is extracted, and the second gain value corresponding to that pitch angle node in the second gain value sequence is extracted. The first gain value is multiplied by the first weighting coefficient to obtain a first product, and the second gain value is multiplied by the second weighting coefficient to obtain a second product. The first product and the second product are added to obtain the combined gain value corresponding to the pitch angle node. Linear combination calculations are performed on all identical pitch angle nodes, and all the obtained combined gain values ​​are arranged in ascending order of pitch angle to generate a gain sequence along the principal axis direction of the target profile azimuth, representing a discrete data set of antenna radiation gain varying with pitch angle at the target profile azimuth.

[0052] For example, if the relative position ratio of the first beam is 0.5, subtracting the relative position ratio of 0.5 from the value 1 yields a first weighting coefficient of 0.5, which is then used as the second weighting coefficient. Taking a pitch angle node of 10° as an example, assuming the first gain value corresponding to a pitch angle of 10° in the first gain value sequence is 30 dB, and the second gain value corresponding to a pitch angle of 10° in the second gain value sequence is 32 dB, multiplying the first gain value of 30 dB by the first weighting coefficient of 0.5 yields a first product of 15 dB. Multiplying the second gain value of 32 dB by the second weighting coefficient of 0.5 yields a second product of 16 dB. Adding the first product of 15 dB and the second product of 16 dB yields a combined gain value of 31 dB corresponding to a pitch angle of 10°. The linear combination calculation is performed by iterating through all the same elevation angle nodes (such as 8°, 9°, 10°, 11°, 12°) in the first and second gain value sequences. All the combined gain values ​​are then arranged in ascending order of elevation angle to generate the first beam gain sequence along the main axis direction of 33.5° azimuth of the target profile.

[0053] Step 2043: Using the main lobe reference as the center of the gain sequence in the main axis direction, extract the gain within a preset step size range on both sides of the main lobe reference in the gain sequence in the main axis direction, and keep the original relative order of pitch angles to obtain an interval-constrained gain sequence centered on the pitch angle of the main lobe peak.

[0054] Optionally, the ship management device subtracts a preset step size from the main lobe peak elevation angle to obtain the lower limit elevation angle, and adds the preset step size to the main lobe peak elevation angle to obtain the upper limit elevation angle. The preset step size is a pre-defined angular span value used to truncate the main lobe and adjacent side lobe regions. In the main axis direction gain sequence, all combined gain values ​​with elevation angle values ​​greater than or equal to the lower limit elevation angle and less than or equal to the upper limit elevation angle are selected. All selected combined gain values ​​are arranged in ascending order of their original elevation angles in the main axis direction gain sequence to obtain an interval-constrained gain sequence centered on the main lobe peak elevation angle. This interval-constrained gain sequence removes irrelevant side lobe data far from the main lobe and retains antenna gain data directly related to the beam coverage area and adjacent interference areas.

[0055] For example, the main lobe peak elevation angle of the first beam is 10° (i.e., the main lobe reference), and the preset step size is set to 6°. Subtracting the preset step size of 6° from the main lobe peak elevation angle of 10° yields a lower limit elevation angle of 4°. Adding the preset step size of 6° to the main lobe peak elevation angle of 10° yields an upper limit elevation angle of 16°. In the main axis direction gain sequence of the first beam, all combined gain values ​​with elevation angles greater than or equal to 4° and less than or equal to 16° are selected. Assuming that the selected combined gain values ​​correspond to elevation angles of 4°, 5°, 6° to 15°, 16° respectively, these combined gain values ​​are arranged in their original relative order from smallest to largest elevation angle to obtain the interval-constrained gain sequence of the first beam centered at the main lobe peak elevation angle of 10°.

[0056] Step 2044: Connect adjacent gains in the interval-constrained gain sequence based on the increasing order of pitch angle to construct a gain variation curve along the principal axis.

[0057] Optionally, the ship management device reads the first combined gain value and its corresponding pitch angle in the interval-constrained gain sequence, using it as the starting data point. Following the increasing order of pitch angles, subsequent combined gain values ​​and their corresponding pitch angles in the interval-constrained gain sequence are read sequentially, serving as subsequent data points. For each pair of adjacent data points, in a two-dimensional coordinate system composed of pitch angles and gain values, the preceding and following data points are connected by a straight line segment. This connection operation is performed on all adjacent data points in the interval-constrained gain sequence, connecting all the straight line segments end-to-end to construct a gain variation curve along the principal axis. The gain variation curve, with the angle of deviation from the main lobe peak pitch angle as the abscissa and the antenna radiation gain as the ordinate, reflects the continuous variation characteristics of the antenna's radiation gain in the target profile azimuth.

[0058] For example, the first combined gain value and its corresponding pitch angle of 4° are read from the interval-constrained gain sequence of the first beam, and this is taken as the starting data point. Following the increasing pitch angle order, subsequent pitch angles of 5°, 6°, up to 16°, and their corresponding combined gain values ​​are read sequentially. For each pair of adjacent data points (e.g., the data point corresponding to pitch angle 4° and the data point corresponding to pitch angle 5°), the preceding and following data points are connected by a straight line segment in a two-dimensional coordinate system composed of pitch angle and gain value. This connection operation is performed on all adjacent data points in the interval-constrained gain sequence of the first beam, connecting all the straight line segments end-to-end to construct the gain variation curve of the first beam along the principal axis.

[0059] The embodiments of the present invention achieve accurate reconstruction from discrete radiation pattern data to continuous profile gain curves, ensuring that the gain variation curves can realistically and continuously reflect the antenna radiation characteristics along the main axis of the gathering of ships on the sea surface, and improving the accuracy of single-satellite multi-ship mixed beam crosstalk modeling.

[0060] Optionally, steps 205 to 208 include: Step 205: Based on the centroid coordinates of each beam and the satellite orbit beam pointing direction, calculate the geographic deflection angle of the centroid coordinates relative to the beam center axis, and convert the geographic deflection angle into the relative elevation angle in the antenna body coordinate system to obtain the centroid reference angle.

[0061] Optionally, the ship management device obtains the satellite orbit beam pointing, which includes the coordinates of the ground projection point of the beam center obtained in step 10.

[0062] The ship management device calculates the straight-line distance on the ground between the centroid coordinates and the ground projection point coordinates of the beam center. Dividing this straight-line distance by the satellite orbital altitude yields the geographic deflection angle, which represents the geocentric angle by which the centroid coordinates deviate from the beam center axis. The geographic deflection angle is then mapped to the attitude deflections (including roll, pitch, and yaw angles) obtained in step 201 using coordinate rotation. This mapping transforms the geographic deflection angle from the geographic coordinate system to the antenna body coordinate system, yielding the relative pitch angle. This relative pitch angle is used as the centroid reference angle, representing the pitch angle by which the spatial center of the ship's distribution deviates from the beam center axis in the antenna body coordinate system.

[0063] For example, taking the first beam as an example, the centroid coordinates of the first beam are (112.52°, 2.15°), the ground projection coordinates of the beam center in the direction of the satellite orbit beam are (112.5°, 2.1°), and the satellite orbit altitude is 35786 km. The calculated straight-line distance between the centroid coordinates and the ground projection coordinates of the beam center is 5.56 km. Dividing the straight-line distance of 5.56 km by the satellite orbit altitude of 35786 km, we get a geographic deflection angle of 0.0089°. We then perform coordinate rotation mapping calculations with the roll angle of 2°, elevation angle of -1°, and yaw angle of 3° obtained in step 201, transforming them to the antenna body coordinate system, and obtain a relative elevation angle of 1.2°. We use the relative elevation angle of 1.2° as the centroid reference angle of the first beam.

[0064] Step 206: Project the spread span of each beam onto the principal axis direction of the antenna body coordinate system, determine the equivalent principal axis spread angle width, and analyze the starting and ending angles of the interference influence area based on the equivalent principal axis spread angle width with the centroid reference angle as the center, to obtain the angle boundary of the interference gain distribution interval.

[0065] Optionally, the ship management device extracts the principal axis span used in calculating the dispersion span, divides the principal axis span by the satellite orbital altitude to obtain the geocentric angle of the principal axis dispersion, combines the geocentric angle of the principal axis dispersion with the attitude deflection in step 201 for coordinate rotation mapping, and projects it onto the principal axis direction of the antenna body coordinate system to obtain the equivalent principal axis dispersion angle width. This equivalent principal axis dispersion angle width represents the pitch angle span occupied by the clustering range of the ship distribution in the antenna body coordinate system. Dividing the equivalent principal axis dispersion angle width by the value 2, the half-width angle is obtained. The ship management device subtracts the half-width angle from the centroid reference angle to obtain the starting angle, and adds the half-width angle to the centroid reference angle to obtain the ending angle. The starting angle and the ending angle are used as the angular boundaries of the interference gain distribution range.

[0066] For example, the main axis span of the first beam is 10 kilometers, and the satellite orbital altitude is 35,786 kilometers. Dividing the main axis span of 10 kilometers by the satellite orbital altitude of 35,786 kilometers, we get a geocentric angle of 0.016° for the main axis dispersion.

[0067] The geocentric angle of the principal axis dispersion of 0.016° is combined with attitude deflection for coordinate rotation mapping and projected onto the principal axis direction of the antenna body coordinate system, resulting in an equivalent principal axis dispersion angle width of 2.4°. Dividing the equivalent principal axis dispersion angle width of 2.4° by the value 2, we get a half-width angle of 1.2°. Subtracting the half-width angle of 1.2° from the centroid reference angle of 1.2°, we get a starting angle of 0°. Adding the half-width angle of 1.2° to the centroid reference angle of 1.2°, we get a ending angle of 2.4°. The starting angle of 0° and the ending angle of 2.4° are used as the angular boundaries of the interference gain distribution range of the first beam.

[0068] Step 207: Find the gain corresponding to the centroid reference angle in the gain change curve to obtain the centroid position reference gain, and find the gain corresponding to the angle boundary in the gain change curve to obtain the interference reference gain.

[0069] Optionally, the ship management device finds an angle node in the horizontal axis of the gain change curve that is equal to the reference angle of the centroid, extracts the vertical axis gain value corresponding to the angle node, and uses the vertical axis gain value as the reference gain of the centroid position. The reference gain of the centroid position characterizes the antenna radiation gain level at the location of the spatial concentration center of the ship distribution.

[0070] The ship management device finds two angle nodes on the horizontal axis of the gain change curve that are equal to the starting angle and the ending angle, respectively, extracts the vertical axis gain values ​​corresponding to these two angle nodes, and uses these two vertical axis gain values ​​as the interference reference gain. This interference reference gain characterizes the antenna radiation gain level at the edge of the gathering range of the ship distribution.

[0071] For example, read the gain variation curve of the first beam, find the angle node on the horizontal axis of the gain variation curve that is equal to the centroid reference angle of 1.2°, and extract the corresponding vertical axis gain value of 28 dB. Use 28 dB as the reference gain for the centroid position of the first beam. Find the angle node on the horizontal axis of the gain variation curve that is equal to the starting angle of 0°, and extract the corresponding vertical axis gain value of 30 dB; find the angle node that is equal to the ending angle of 2.4°, and extract the corresponding vertical axis gain value of 25 dB. Use 30 dB and 25 dB as the interference reference gain for the first beam.

[0072] Step 208: Perform interval mapping based on the centroid position reference gain and the interference reference gain to obtain the target gain distribution interval.

[0073] Optionally, the ship management device performs interval mapping based on the centroid position reference gain and the interference reference gain to obtain the target gain distribution interval, as described in steps 2081 to 2083.

[0074] The embodiments of the present invention realize the adaptive coupling between the geometric features of the non-uniform aggregation of ships on the sea surface and the physical characteristics of the far-field radiation pattern of the satellite antenna, ensuring that the target gain distribution range can be realistically and accurately defined to determine the specific angular range of the equivalent interference source in the sidelobe or main lobe region of the antenna, thereby improving the accuracy of single-satellite multi-ship mixed beam crosstalk modeling.

[0075] Optionally, the process of steps 2081 to 2083 includes: Step 2081: Compare the gain magnitudes based on the start boundary gain and the end boundary gain in the interference reference gain to obtain the lower limit gain and the upper limit gain of interference.

[0076] Optionally, the ship management device extracts the interference reference gain, which includes the initial boundary gain corresponding to the starting angle and the termination boundary gain corresponding to the ending angle. The values ​​of the initial boundary gain and the termination boundary gain are compared. If the value of the initial boundary gain is less than or equal to the value of the termination boundary gain, the initial boundary gain is used as the lower limit interference gain, and the termination boundary gain is used as the upper limit interference gain. If the value of the initial boundary gain is greater than the value of the termination boundary gain, the termination boundary gain is used as the lower limit interference gain, and the initial boundary gain is used as the upper limit interference gain. The lower limit interference gain represents the minimum antenna radiation gain value corresponding to the equivalent interference source within the target gain distribution range, and the upper limit interference gain represents the maximum antenna radiation gain value corresponding to the equivalent interference source within the target gain distribution range.

[0077] For example, taking the first beam as an example, in the interference reference gain of the first beam, the starting boundary gain corresponding to the starting angle of 0° is 30 dB, and the ending boundary gain corresponding to the ending angle of 2.4° is 25 dB. Comparing the starting boundary gain of 30 dB and the ending boundary gain of 25 dB, since the starting boundary gain of 30 dB is greater than the ending boundary gain of 25 dB, the ending boundary gain of 25 dB is taken as the lower limit interference gain of the first beam, and the starting boundary gain of 30 dB is taken as the upper limit interference gain of the first beam.

[0078] Step 2082: Using the centroid position reference gain as the reference zero point, determine the negative gain deviation based on the difference between the lower limit gain of interference and the centroid position reference gain, and determine the positive gain deviation based on the difference between the upper limit gain of interference and the centroid position reference gain.

[0079] Optionally, the ship management device sets the value of the centroid position reference gain as the reference zero point, subtracts the value of the lower limit of interference gain from the value of the centroid position reference gain, and uses the difference as the negative gain deviation. This negative gain deviation characterizes the downward attenuation of the equivalent interference source distribution edge relative to the spatial concentration center of the ship distribution in the gain dimension.

[0080] The ship management device performs a subtraction operation by subtracting the value of the upper limit gain of the interference from the value of the reference gain of the centroid position, and uses the difference as the positive gain deviation. This positive gain deviation characterizes the upward enhancement of the equivalent interference source distribution edge relative to the spatial concentration center of the ship distribution in the gain dimension.

[0081] For example, the centroid position reference gain of the first beam is 28 dB, the lower interference limit gain is 25 dB, and the upper interference limit gain is 30 dB. Setting the centroid position reference gain of 28 dB as the reference zero, subtracting the lower interference limit gain of 25 dB from the centroid position reference gain of 28 dB yields a difference of -3 dB, which is taken as the negative gain deviation of the first beam. Subtracting the upper interference limit gain of 30 dB from the centroid position reference gain of 28 dB yields a difference of 2 dB, which is taken as the positive gain deviation of the first beam.

[0082] Step 2083: Based on the negative gain deviation and positive gain deviation analysis, the gain fluctuation range of the equivalent interference source relative to the centroid position is obtained to obtain the target gain distribution interval.

[0083] Optionally, in a two-dimensional coordinate system composed of relative gain value and cumulative probability distribution, the ship management device defines a continuous numerical range from the lower to the upper boundary of the relative gain value dimension, using the value corresponding to the negative gain deviation as the lower boundary and the value corresponding to the positive gain deviation as the upper boundary. The ship management device sets the lower boundary of the cumulative probability distribution dimension to 0 and the upper boundary to 1, defining a continuous probability range from 0 to 1. This continuous numerical range in the relative gain value dimension is combined with the continuous probability range in the cumulative probability distribution dimension to construct a two-dimensional rectangular region, which is then used as the target gain distribution interval. This target gain distribution interval defines the gain fluctuation range of the equivalent interference source using both the relative gain value and the cumulative probability distribution.

[0084] For example, the negative gain deviation of the first beam is -3 dB, and the positive gain deviation is 2 dB. In a two-dimensional coordinate system composed of relative gain values ​​and cumulative probability distribution, the negative gain deviation of -3 dB is used as the lower boundary of the relative gain value dimension, and the positive gain deviation of 2 dB is used as the upper boundary of the relative gain value dimension, defining a continuous numerical range from -3 dB to 2 dB in the relative gain value dimension. The lower boundary of the cumulative probability distribution dimension is set to 0, and the upper boundary is set to 1, defining a continuous probability range from 0 to 1 in the cumulative probability distribution dimension. Combining the continuous numerical range from -3 to 2 dB in the relative gain value dimension with the continuous probability range from 0 to 1 in the cumulative probability distribution dimension constructs a two-dimensional rectangular region, which is used as the target gain distribution interval for the first beam.

[0085] The embodiments of the present invention achieve a precise conversion and definition from absolute gain to relative gain fluctuation range, ensuring that the target gain distribution range can fully and realistically reflect the gain fluctuation characteristics of the equivalent interference source relative to the centroid position under non-uniform distribution, and improve the accuracy of single-satellite multi-ship mixed beam crosstalk modeling.

[0086] Optionally, the process of step 404 in step 401 includes: Step 401: Determine the effective angle range of the gain variation curve based on the principal axis direction angle and the scattering span, and adaptively discretize the effective angle range based on the user distribution probability density of the effective angle range to generate a discrete angle slice sequence in which the angle sampling point spacing changes with the user distribution probability density.

[0087] Optionally, the ship management device divides the dispersion span by the satellite orbital altitude to obtain the geographic span angle. This geographic span angle is then combined with attitude deflection for coordinate rotation mapping and projected onto the principal axis of the antenna's coordinate system to obtain the effective angular span. On the horizontal axis of the gain variation curve, with the centroid reference angle as the center, half of the effective angular span is extended to both sides to define a continuous angular range. This continuous angular range is taken as the effective angular interval, which characterizes the actual angular range occupied by the ship clustered distribution in the pitch dimension of the antenna's coordinate system.

[0088] A baseline sampling step size and a probability density threshold are set. The ship management device acquires the user distribution probability density within the effective angle interval. The user distribution probability density characterizes the density of ship clustering within a unit angle range. For each local angle sub-interval within the effective angle interval, it is determined whether the user distribution probability density within that local angle sub-interval is greater than or equal to the probability density threshold. If it is greater than or equal to the probability density threshold, the baseline sampling step size is divided by 2 to obtain the dense sampling step size, and the local angle sub-interval is divided at equal intervals using this dense sampling step size. If it is less than the probability density threshold, the local angle sub-interval is divided at equal intervals using the baseline sampling step size. The sampling points obtained from all the local angle sub-interval divisions are merged and arranged in ascending order of angle to generate a discrete angle slice sequence. The spacing between two adjacent angle sampling points in the discrete angle slice sequence decreases as the user distribution probability density increases.

[0089] For example, taking the first beam as an example, the first beam has a dispersion span of 10 kilometers, a satellite orbital altitude of 35,786 kilometers, and a centroid reference angle of 1.2°. Dividing the dispersion span of 10 kilometers by the satellite orbital altitude of 35,786 kilometers yields a geographic span angle of 0.016°. Combining this geographic span angle of 0.016° with attitude deflection for coordinate rotation mapping, we obtain an effective angular span of 2.4°. On the horizontal axis of the gain variation curve of the first beam, with the centroid reference angle of 1.2° as the center, we extend half of the effective angular span of 2.4° (i.e., 1.2°) to both sides, defining a continuous angular range from 0° to 2.4° as the effective angular interval. We obtain the user distribution probability density within the effective angular interval, setting the baseline sampling step size to 0.2° and the probability density threshold to 5 Hz per degree. Assuming that the user distribution probability density is 8 vessels per degree within the local angle sub-interval of 0.8° to 1.6°, which is greater than the probability density threshold of 5, the baseline sampling step size of 0.2° is divided by the value 2 to obtain a dense sampling step size of 0.1°, and the local angle sub-interval is divided at intervals of 0.1°. Within the local angle sub-intervals of 0° to 0.8° and 1.6° to 2.4°, the user distribution probability density is 3 vessels per degree, which is less than the probability density threshold of 5. The ship management device directly divides the sub-intervals at intervals of the baseline sampling step size of 0.2°, merges and arranges all sampling points, and generates the discrete angle slice sequence of the first beam.

[0090] Step 402: Based on the beam center axis azimuth, map the relative electronic scanning angle corresponding to each discrete angle slice in the discrete angle slice sequence to the interference incident azimuth angle in the geographic coordinate system.

[0091] Optionally, the ship management device traverses each discrete angle slice in the discrete angle slice sequence, extracts the angle corresponding to the discrete angle slice, and uses the angle as the relative electronic scanning angle. The relative electronic scanning angle represents the pitch angle of the discrete angle slice in the antenna body coordinate system that deviates from the pitch angle of the main lobe peak.

[0092] The ship management device acquires the azimuth of the beam center axis, which includes the beam center axis azimuth angle. The relative electronic scanning angle and attitude deflection (including roll, pitch, and yaw angles) are calculated using a reverse coordinate rotation mapping. The relative electronic scanning angle is transformed from the antenna coordinate system to the geographic coordinate system to obtain the geographic deflection angle. Using the ground projection point coordinates of the beam center as the reference point and the beam center axis azimuth angle as the reference direction, spatial geometric calculations are performed, combining the geographic deflection angle and satellite orbital altitude, to determine the geographic projection position of this discrete angle slice on the Earth's surface.

[0093] The ship management device calculates the geographic azimuth angle of the geographic projection position relative to the reference point, and uses this geographic azimuth angle as the interference incident azimuth angle corresponding to the discrete angle slice. This interference incident azimuth angle characterizes the horizontal incident direction of the equivalent interference source relative to the center of the interfered beam in the geographic coordinate system.

[0094] For example, taking a discrete angle slice with an angle of 1° in the discrete angle slice sequence of the first beam as an example, the ship management device extracts the relative electronic scanning angle corresponding to this discrete angle slice as 1°. The azimuth angle of the beam center axis of the first beam is obtained as 45°, and the coordinates of the ground projection point of the beam center are (112.5°, 2.1°). The relative electronic scanning angle of 1° is calculated by performing a reverse coordinate rotation mapping with the roll angle of 2°, the pitch angle of -1°, and the yaw angle of 3°, and then transformed to the geographic coordinate system to obtain the geographic deflection angle of 0.8°.

[0095] Using the ground projection point coordinates (112.5°, 2.1°) of the beam center as the reference point and the azimuth angle of the beam center axis of 45° as the reference direction, combined with the geographic deflection angle of 0.8° and the satellite orbital altitude of 35786 km, spatial geometric calculations are performed to determine the geographic projection position of the discrete angle slice on the Earth's surface. The geographic azimuth angle of this geographic projection position relative to the reference point is calculated to be 42°, and 42° is taken as the interference incident azimuth angle corresponding to this discrete angle slice.

[0096] Step 403: Based on the comparison between each interference incident azimuth angle and the expected signal receiving pointing angle corresponding to the expected signal coupling gain of the interfered beam, the receiving deflection angle of each interference incident azimuth angle is obtained.

[0097] Optionally, the ship management device acquires the desired signal receiving pointing angle corresponding to the desired signal coupling gain of the interfered beam. The desired signal receiving pointing angle characterizes the horizontal pointing angle of the main lobe of the receiving antenna of the interfered beam in the geographic coordinate system when receiving the desired signal. For each interference incident azimuth angle, the absolute value of the difference between the numerical value of the interference incident azimuth angle and the numerical value of the desired signal receiving pointing angle is taken as the receiving deflection angle of that interference incident azimuth angle. This receiving deflection angle characterizes the horizontal angular deviation of the incident direction of the equivalent interference source from the pointing direction of the main lobe of the receiving antenna of the interfered beam.

[0098] For example, suppose the desired signal receiving pointing angle corresponding to the desired signal coupling gain of the interfered beam is 40°. Taking a discrete angle slice in the first beam with an interference incident azimuth angle of 42° as an example, subtract the desired signal receiving pointing angle of 40° from the interference incident azimuth angle of 42°, and the difference is 2°. Taking the absolute value of the difference 2°, we get 2°, and use 2° as the receiving deflection angle of the interference incident azimuth angle, that is, the receiving deflection angle of the interference incident azimuth angle is 2°.

[0099] Step 404: Match the receiving antenna gain for each receiving deflection angle in the receiving antenna pattern of the interfered beam, and perform gain inversion based on the equivalent interference coupling gain and the receiving antenna gain for each interference incident azimuth angle to obtain the hybrid beam crosstalk modeling result.

[0100] Optionally, the ship management device acquires the receiving antenna pattern of the interfered beam, and finds the antenna gain value corresponding to each receiving deflection angle in the receiving antenna pattern, which is the receiving antenna gain. The receiving antenna pattern refers to a two-dimensional or three-dimensional mathematical model or dataset characterizing the signal reception capability (i.e., antenna gain) distribution of the receiving antenna of the interfered beam in different spatial incident directions. The ship management device performs gain inversion based on the equivalent interference coupling gain and the receiving antenna gain at each interference incident azimuth angle to obtain the hybrid beam crosstalk modeling result, as detailed in steps 4041 to 4044.

[0101] The embodiments of the present invention realize end-to-end accurate estimation of interference levels from the non-uniform geometric distribution of ships on the sea surface to the system level, overcome the crosstalk assessment bias caused by the traditional uniform distribution assumption, and improve the accuracy of crosstalk modeling of single-satellite multi-ship mixed beams.

[0102] Optionally, the processes of steps 4041 to 4044 include: Step 4041: Discretely accumulate and aggregate the receiving antenna gain, the transmitting antenna gain at the corresponding position in the discrete angle slice sequence, and the density at the corresponding position in the discrete angle slice sequence for each interference incident azimuth angle along the angle domain to obtain the antenna response matching degree.

[0103] Optionally, the ship management device traverses each discrete angle slice in the discrete angle slice sequence. For the current discrete angle slice, it obtains the receiving antenna gain matched to the receiving antenna pattern of the interfered beam at the interference incident azimuth angle corresponding to the discrete angle slice, and converts the receiving antenna gain into a linear power ratio value. It then obtains the transmitting antenna gain corresponding to the discrete angle slice on the gain variation curve, converts the transmitting antenna gain into a linear power ratio value, and obtains the user probability density at the corresponding location of the discrete angle slice. The ship management device multiplies the linear power ratio value of the receiving antenna gain, the linear power ratio value of the transmitting antenna gain, and the user probability density to obtain the local response product of the current discrete angle slice. It then multiplies the angle sampling point spacing (i.e., the angle difference between two adjacent angle sampling points) of the current discrete angle slice with the local response product to obtain the weighted response value of the current discrete angle slice. After traversing all discrete angle slices in the discrete angle slice sequence, the ship management device accumulates the weighted response values ​​of all discrete angle slices, and uses the sum obtained from the accumulation as the antenna response matching degree. The antenna response matching degree characterizes the overall energy coupling matching level in the angular domain of the spatial radiation characteristics of the transmitting antenna of the interfering beam, the non-uniform spatial distribution characteristics of ships on the sea surface, and the spatial filtering characteristics of the receiving antenna of the interfering beam.

[0104] For example, taking a discrete angle slice with an angle value of 1° in the discrete angle slice sequence of the first beam as an example, the angle sampling point spacing of this discrete angle slice is 0.1°. The receiving antenna gain matched to the receiving antenna pattern of the interfered beam at the interference incident azimuth angle of 42° corresponding to this discrete angle slice is obtained and converted to a linear power ratio of 0.8. The transmitting antenna gain corresponding to this discrete angle slice on the gain variation curve is obtained and converted to a linear power ratio of 0.6. The user distribution probability density at the corresponding location of this discrete angle slice is obtained as 8 units per degree.

[0105] Multiplying the linear power ratio of the receive antenna gain (0.8), the linear power ratio of the transmit antenna gain (0.6), and the user probability density (8) yields a local response product of 3.84. Multiplying the angle sampling point spacing (0.1) by the local response product 3.84 yields a weighted response value of 0.384 for this discrete angle slice. This calculation is performed on all discrete angle slices in the first beam's discrete angle slice sequence, and the weighted response values ​​of all discrete angle slices are summed. Assuming the sum is 4.5, this 4.5 is taken as the antenna response matching degree of the first beam.

[0106] Step 4042: Based on the antenna response matching degree and the equivalent interference coupling gain, determine the total equivalent interference coupling strength, and then compare the total equivalent interference coupling strength with the desired signal coupling gain to obtain the interference level center relative to the interference level.

[0107] Optionally, the equivalent interference coupling gain characterizes the reference interference power generated by a single standard ship terminal on the interfered beam under ideal channel conditions, and the desired signal coupling gain characterizes the desired signal power received by the receiver of the interfered beam. The ship management device multiplies the equivalent interference coupling gain by the antenna response matching degree, and uses the product as the total equivalent interference coupling strength. This total equivalent interference coupling strength characterizes the total interference power exerted on the receiver of the interfered beam by all non-uniformly distributed ship terminals within the coverage area of ​​the interfered beam. The ship management device divides the total equivalent interference coupling strength by the desired signal coupling gain, and uses the quotient as the interference level center relative to the interference level. This interference level center characterizes the center reference ratio of the total interference power to the desired signal power under deterministic spatial distribution and deterministic antenna response conditions.

[0108] For example, suppose the equivalent interference coupling gain of the first beam is 2 milliwatts, and the desired signal coupling gain of the interfered beam is 500 milliwatts. Multiply the equivalent interference coupling gain of 2 milliwatts by the antenna response matching degree of 4.5 to obtain a product of 9 milliwatts. Take 9 milliwatts as the total equivalent interference coupling strength of the first beam. Divide the total equivalent interference coupling strength of 9 milliwatts by the desired signal coupling gain of 500 milliwatts to obtain a quotient of 0.018. Take 0.018 as the interference level center of the relative interference level of the first beam.

[0109] Step 4043: Map the interference level center to the interval boundary based on the boundary range of the target gain distribution interval to obtain the fluctuation boundary range of the relative interference level.

[0110] Optionally, the ship management device acquires the lower boundary (i.e., negative gain deviation) and upper boundary (i.e., positive gain deviation) of the target gain distribution range in the dimension of relative gain value.

[0111] The ship management device uses 10 as the base, divides the negative gain deviation by 10, and uses the quotient as the exponent for exponential operation to obtain the lower limit linear scaling factor. Using 10 as the base, it divides the positive gain deviation by 10, and uses the quotient as the exponent for exponential operation to obtain the upper limit linear scaling factor. The ship management device multiplies the interference level center by the lower limit linear scaling factor, and uses the product as the lower limit fluctuation boundary relative to the interference level. It also multiplies the interference level center by the upper limit linear scaling factor, and uses the product as the upper limit fluctuation boundary relative to the interference level.

[0112] The ship management system combines the lower and upper fluctuation boundaries to obtain the fluctuation boundary range of the relative interference level. This fluctuation boundary range characterizes the dynamic range of possible changes in the relative interference level under the influence of uncertainties in the ship's spatial location and antenna gain fluctuations.

[0113] For example, the target gain distribution range of the first beam has a lower limit boundary (negative gain deviation) of -3 dB and an upper limit boundary (positive gain deviation) of 2 dB in the relative gain value dimension, with an interference level center of 0.018. Using 10 as the base, the quotient of -0.3 (negative gain deviation -3 dB) divided by 10 is used as the exponent for exponential operation, resulting in a lower limit linear scaling factor of approximately 0.501. Using 10 as the base, the quotient of 0.2 (positive gain deviation 2 dB) divided by 10 is used as the exponent for exponential operation, resulting in an upper limit linear scaling factor of approximately 1.585. Multiplying the interference level center of 0.018 by the lower limit linear scaling factor of 0.501 yields a product of approximately 0.009, which is taken as the lower limit fluctuation boundary of the relative interference level of the first beam. Multiplying the interference level center of 0.018 by the upper limit linear scaling factor of 1.585 yields a product of approximately 0.0285. This 0.0285 is used as the upper limit fluctuation boundary for the relative interference level of the first beam. Combining the lower limit fluctuation boundary of 0.009 and the upper limit fluctuation boundary of 0.0285, the fluctuation boundary range for the relative interference level of the first beam is [0.009, 0.0285].

[0114] Step 4044: Based on the interference level center and fluctuation boundary range, determine the hybrid beam crosstalk modeling results.

[0115] Optionally, the ship management device uses the interference level center as the nominal evaluation value of the hybrid beam crosstalk modeling result, uses the fluctuation boundary range as the confidence interval of the hybrid beam crosstalk modeling result, and outputs the nominal evaluation value and the confidence interval together as the hybrid beam crosstalk modeling result.

[0116] The nominal evaluation value refers to the benchmark value reflecting the degree of interference in the system, calculated under ideal deterministic conditions that do not consider gain fluctuations and position deviations.

[0117] The confidence interval refers to the range of values ​​within which the system's disturbance level actually falls after considering the gain fluctuations and spatial location uncertainties caused by the non-uniform distribution of ships. It is used to assess the reliability of the results and the risk of fluctuations.

[0118] For example, the interference level center value of 0.018 for the first beam is used as the nominal evaluation value of the hybrid beam crosstalk modeling result, and the fluctuation boundary range of the first beam [0.009, 0.0285] is used as the confidence interval of the hybrid beam crosstalk modeling result. The nominal evaluation value of 0.018 and the confidence interval [0.009, 0.0285] are combined and output as the final hybrid beam crosstalk modeling result for the first beam.

[0119] The embodiments of the present invention realize the transformation from deterministic interference level calculation to uncertain interference fluctuation range assessment, ensuring that the hybrid beam crosstalk modeling results can not only provide accurate nominal interference assessment values, but also fully reveal the interference fluctuation risks caused by non-uniform ship distribution, thereby improving the accuracy of single-satellite multi-ship hybrid beam crosstalk modeling.

[0120] Furthermore, the single-satellite multi-ship hybrid beam crosstalk modeling device based on the distribution of sea surface user areas provided by the present invention will be described below. The single-satellite multi-ship hybrid beam crosstalk modeling device based on the distribution of sea surface user areas described below can be referred to in correspondence with the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of sea surface user areas described above.

[0121] Optionally, refer to Figure 2 , Figure 2 This is a schematic diagram of the single-satellite multi-ship hybrid beam crosstalk modeling device based on sea surface user area distribution provided by the present invention. The single-satellite multi-ship hybrid beam crosstalk modeling device based on sea surface user area distribution includes: The user distribution analysis module 210 is used to perform beam geographic projection calculation based on satellite orbit ephemeris data and antenna pointing parameters to obtain the coverage boundary range and beam center axis orientation of each beam. Based on each coverage boundary range and ship historical trajectory points, it performs analysis to obtain the principal axis direction angle, centroid coordinates and dispersion span of the user distribution.

[0122] The gain interval mapping module 220 is used to cross-cut the far-field radiation pattern of the satellite antenna based on the azimuth of the beam center axis and the direction angle of the main axis, to obtain the gain variation curve along the main axis direction, and to perform interval mapping based on the centroid coordinates, scattering span and gain variation curve to obtain the target gain distribution interval of the equivalent interference source.

[0123] The interference gain coupling module 230 is used to perform energy integration based on the target gain distribution range and gain change curve to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam.

[0124] The gain inversion module 240 is used to perform gain inversion based on the equivalent interference coupling gain and the expected signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

[0125] The embodiments of the present invention improve the accuracy of single-satellite multi-ship hybrid beam crosstalk modeling.

[0126] Please see Figure 3 , Figure 3 An embodiment diagram of an electronic device provided in accordance with the present invention. For example... Figure 3 As shown, an embodiment of the present invention provides an electronic device 300, including a memory 310, a processor 320, and a computer program 311 stored in the memory 310 and executable on the processor 320. When the processor 320 executes the computer program 311, it implements the processes of steps 10 to 40.

[0127] Please see Figure 4 , Figure 4 An embodiment diagram of a computer-readable storage medium provided in accordance with an embodiment of the present invention is shown. Figure 4 As shown, this embodiment provides a computer-readable storage medium 400 on which a computer program 311 is stored. When the computer program 311 is executed by a processor, it implements the processes of steps 10 to 40.

[0128] On the other hand, the present invention also provides a computer program product, which includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer is able to execute the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface provided by the above methods, which includes steps 10 to 40.

[0129] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0130] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0131] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to depart from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for modeling crosstalk between a single satellite and multiple ships using hybrid beams based on the distribution of user areas on the sea surface, characterized in that, include: Based on satellite orbit ephemeris data and antenna pointing parameters, beam geographic projection calculation is performed to obtain the coverage boundary range and beam center axis orientation of each beam. Based on each coverage boundary range and ship historical trajectory points, analysis is performed to obtain the main axis direction angle, centroid coordinates and dispersion span of user distribution. Based on the azimuth of the beam center axis and the direction angle of the main axis, the far-field radiation pattern of the satellite antenna is profiled to obtain the gain variation curve along the main axis direction. Based on the centroid coordinates, the dispersion span and the gain variation curve, interval mapping is performed to obtain the target gain distribution interval of the equivalent interference source. Based on the target gain distribution range and gain change curve, energy integration is performed to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam. Gain inversion is performed based on the equivalent interference coupling gain and the desired signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

2. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 1, characterized in that, The hybrid beam crosstalk modeling results are obtained, including: The effective angle range of the gain change curve is defined based on the main axis direction angle and the dispersion span, and the effective angle range is adaptively discretized based on the user distribution probability density of the effective angle range to generate a discrete angle slice sequence in which the angle sampling point spacing changes with the user distribution probability density. Based on the azimuth of the beam center axis, the relative electronic scanning angle corresponding to each discrete angle slice in the discrete angle slice sequence is mapped to the interference incident azimuth angle in the geographic coordinate system. The receiving deflection angle of each interference incident azimuth angle is obtained by comparing the expected signal receiving pointing angle corresponding to the expected signal coupling gain of the interfered beam with the expected incident azimuth angle of each interference incident azimuth angle. Match the receiving antenna gain for each receiving deflection angle in the receiving antenna pattern of the interfered beam, and perform gain inversion based on the equivalent interference coupling gain and the receiving antenna gain for each interference incident azimuth angle to obtain the hybrid beam crosstalk modeling result.

3. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 2, characterized in that, The gain inversion based on the equivalent interference coupling gain and the receiving antenna gain at each interference incident azimuth angle yields the hybrid beam crosstalk modeling results, including: Along the angular domain, the receiving antenna gain at each incident azimuth angle of interference, the transmitting antenna gain at the corresponding position in the discrete angular slice sequence, and the density at the corresponding position in the discrete angular slice sequence are discretely accumulated and aggregated to obtain the antenna response matching degree. Based on the antenna response matching degree and the equivalent interference coupling gain, the total equivalent interference coupling strength is determined, and the ratio of the total equivalent interference coupling strength to the desired signal coupling gain is used to obtain the interference level center relative to the interference level. Based on the boundary range of the target gain distribution interval, the center of the interference level is mapped to the interval boundary to obtain the fluctuation boundary range of the relative interference level. Based on the interference level center and the fluctuation boundary range, the hybrid beam crosstalk modeling result is determined.

4. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 1, characterized in that, The process of cross-sectionally extracting the far-field radiation pattern of the satellite antenna based on the azimuth of the beam center axis and the principal axis direction angle to obtain the gain variation curve along the principal axis direction includes: Based on the matching of the beam center axis azimuth angle and the main axis direction angle in the satellite attitude pointing table, the attitude deflection of the satellite antenna body coordinate system relative to the geographic coordinate system at the current moment is obtained. Based on the antenna main lobe pointing table, the main lobe peak elevation angle of the beam center axis in the antenna body coordinate system is analyzed to obtain the main lobe reference. Based on the attitude deflection, the principal axis orientation angle in geographic space is mapped to the antenna body coordinate system to obtain the target profile orientation; Based on the gain corresponding to the elevation angle of two adjacent azimuth slices in the far-field radiation pattern of the satellite antenna with the azimuth of the target profile, the dual-slice gain is determined. Gain analysis was performed based on the main lobe reference and the dual-slice gain to obtain the gain variation curve.

5. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 4, characterized in that, The gain analysis based on the main lobe reference and the dual-slice gain, to obtain the gain change curve, includes: Based on the azimuth difference between the target profile azimuth and two adjacent azimuth slices, the relative position ratio of the target profile azimuth between the two adjacent azimuth slices is determined. Based on the dual-slice gain and the relative position ratio, the gains corresponding to the same pitch angle in the two azimuth slices are linearly combined to generate a gain sequence along the main axis direction of the target profile azimuth. Using the main lobe reference as the center of the main axis direction gain sequence, the gain within a preset step size range on both sides of the main lobe reference is extracted from the main axis direction gain sequence, while maintaining the original relative order of pitch angles, to obtain an interval-constrained gain sequence centered on the main lobe peak pitch angle. Adjacent gains in the interval-constrained gain sequence are connected based on the increasing order of pitch angle to construct a gain variation curve along the principal axis.

6. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 1, characterized in that, The process of performing interval mapping based on the centroid coordinates, the dispersion span, and the gain variation curve to obtain the target gain distribution interval of the equivalent interference source includes: Based on the centroid coordinates of each beam and the beam pointing of the satellite orbit, the geographic deflection angle of the centroid coordinates relative to the beam center axis is calculated, and the geographic deflection angle is converted into the relative elevation angle in the antenna body coordinate system to obtain the centroid reference angle. Project the spread span of each beam onto the principal axis direction of the antenna body coordinate system to determine the equivalent principal axis spread angle width. Using the centroid reference angle as the center, analyze the starting and ending angles of the interference influence area based on the equivalent principal axis spread angle width to obtain the angle boundary of the interference gain distribution range. Find the gain corresponding to the centroid reference angle in the gain variation curve to obtain the centroid position reference gain, and find the gain corresponding to the angle boundary in the gain variation curve to obtain the interference reference gain; The target gain distribution interval is obtained by performing interval mapping based on the centroid position reference gain and the interference reference gain.

7. The single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution according to claim 6, characterized in that, The interval mapping based on the centroid position reference gain and the interference reference gain to obtain the target gain distribution interval includes: Based on the start boundary gain and the end boundary gain in the interference reference gain, the lower limit interference gain and the upper limit interference gain are obtained by comparing the gain magnitudes. Using the centroid position reference gain as a reference zero, a negative gain deviation is determined based on the difference between the lower limit interference gain and the centroid position reference gain, and a positive gain deviation is determined based on the difference between the upper limit interference gain and the centroid position reference gain. Based on the negative gain deviation and the positive gain deviation, the gain fluctuation range of the equivalent interference source relative to the centroid position is analyzed, and the target gain distribution interval is obtained.

8. A single-satellite multi-ship hybrid beam crosstalk modeling device based on sea surface user area distribution, characterized in that, The apparatus is used to implement the single-satellite multi-ship hybrid beam crosstalk modeling method based on sea surface user area distribution as described in any one of claims 1 to 7; the apparatus includes: The user distribution analysis module is used to perform beam geographic projection calculation based on satellite orbit ephemeris data and antenna pointing parameters to obtain the coverage boundary range and beam center axis orientation of each beam. Based on each coverage boundary range and ship historical trajectory points, the module analyzes to obtain the principal axis direction angle, centroid coordinates and dispersion span of the user distribution. The gain interval mapping module is used to cross-section the far-field radiation pattern of the satellite antenna based on the azimuth of the beam center axis and the direction angle of the main axis, to obtain the gain variation curve along the main axis direction, and to perform interval mapping based on the centroid coordinates, the dispersion span and the gain variation curve to obtain the target gain distribution interval of the equivalent interference source. The interference gain coupling module is used to perform energy integration based on the target gain distribution range and gain change curve to obtain the equivalent interference coupling gain of a single interference beam to the interfered beam. The gain inversion module is used to perform gain inversion based on the equivalent interference coupling gain and the expected signal coupling gain of the interfered beam to obtain the hybrid beam crosstalk modeling results for a single satellite and multiple ships.

9. An electronic device, comprising: Memory, used to store computer programs; A processor for reading and executing the computer program, characterized in that, when the processor executes the computer program, it implements the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface as described in any one of claims 1 to 7.

10. A non-transitory computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the single-satellite multi-ship hybrid beam crosstalk modeling method based on the distribution of user areas on the sea surface as described in any one of claims 1 to 7.

Images