Satellite-borne phased array antenna beam control method, system and device

Abstract

The embodiment of the specification provides a satellite-borne phased array antenna beam control method, system and device, wherein the method comprises the following steps: determining initial array information and initial suppression information, and constructing an initial array model based on the initial array information, wherein the initial suppression information comprises a sidelobe suppression window function satisfying a sidelobe earth matching condition; calculating initial array excitation coefficients corresponding to the initial array model by using the initial suppression information, and determining radiation performance information of the initial array model through the initial array excitation coefficients; iteratively optimizing the initial array information and the initial suppression information based on the radiation performance information until a target array model satisfying the sidelobe earth matching condition and target array excitation coefficients of the target array model are obtained, the target array model is used for designing a target antenna array, and the target array excitation coefficients are used for controlling a communication beam of the target antenna array, so that the system and automatic antenna design is realized, and the radiated communication beam has strong anti-interference and compatibility.

Description

Technical Field

[0001] The embodiments in this specification relate to the field of satellite communication technology, and in particular to a method, system and device for beam control of a spaceborne phased array antenna. Background Technology

[0002] With the rapid development of global satellite internet, low-Earth orbit (LEO) satellite communication systems need to provide high-speed data, multimedia, and mobile communication services, which places extremely high demands on the performance of spaceborne phased array antennas. As a key component for user communication throughput, phased array antennas need to possess wide scanning angles, broadband multi-beam characteristics, and low sidelobe characteristics to meet the requirements of wide-area coverage, high-capacity communication, and system-wide anti-interference. In LEO satellite communication scenarios, there is a unique technical challenge: free-space path loss is non-uniformly distributed depending on the geometry of the satellite-to-ground link. Specifically, when the beam (main lobe) points to the edge of the coverage area (large scanning angle), the main lobe propagation path is long, and the path loss is large; however, the sidelobes of the antenna pattern may cover the nadir region where the path loss is smaller. This difference in path loss can partially or even completely offset the suppression effect of the antenna sidelobes, making the satellite communication link susceptible to interference from the nadir region or interfering with existing services in the nadir region. Therefore, how to enable spaceborne phased array antennas to have anti-interference capabilities is a problem that urgently needs to be solved. Summary of the Invention

[0003] In view of this, embodiments of this specification provide a method for beam control of a spaceborne phased array antenna. One or more embodiments of this specification also relate to a spaceborne phased array antenna beam control system, a spaceborne phased array antenna beam control device, a computing device, a computer-readable storage medium, and a computer program product, to address the technical deficiencies existing in the prior art.

[0004] According to a first aspect of the embodiments of this specification, a beam control method for a spaceborne phased array antenna is provided, comprising:

[0005] Determine initial array information and initial suppression information, and construct an initial array model based on the initial array information, wherein the initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition;

[0006] The initial array excitation coefficients corresponding to the initial array model are calculated using the initial suppression information, and the radiation performance information of the initial array model is determined using the initial array excitation coefficients.

[0007] Based on the radiation performance information, the initial array information and the initial suppression information are iteratively optimized until the target array model and the target array excitation coefficients of the target array model that satisfy the sidelobe earth matching condition are obtained. The target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array.

[0008] According to a second aspect of the embodiments of this specification, a spaceborne phased array antenna beam control system is provided. The system includes a beam control component and an antenna array, wherein the antenna array is obtained by designing a target array model determined by the above-described spaceborne phased array antenna beam control method.

[0009] The beam control component, in response to an adjustment command for the target beam angle, determines the target array excitation coefficient corresponding to the target beam angle in the array excitation coefficient library, wherein the array excitation coefficient in the array excitation coefficient library is calculated by the above-described spaceborne phased array antenna beam control method.

[0010] The antenna array is used to transmit the communication beam corresponding to the excitation coefficient of the target array to the target beam angle.

[0011] According to a third aspect of the embodiments of this specification, a beam control device for a spaceborne phased array antenna is provided, comprising:

[0012] The determination module is configured to determine initial array information and initial suppression information, and to construct an initial array model based on the initial array information, wherein the initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition;

[0013] The calculation module is configured to use the initial suppression information to calculate the initial array excitation coefficients corresponding to the initial array model, and to determine the radiation performance information of the initial array model through the initial array excitation coefficients;

[0014] The optimization module is configured to iteratively optimize the initial array information and the initial suppression information based on the radiation performance information until a target array model that satisfies the sidelobe earth matching condition and the target array excitation coefficients of the target array model are obtained. The target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array.

[0015] According to a fourth aspect of the embodiments of this specification, a computing device is provided, comprising:

[0016] Memory and processor;

[0017] The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions. When the computer-executable instructions are executed by the processor, they implement the steps of the above-described spaceborne phased array antenna beam control method.

[0018] According to a fifth aspect of the embodiments of this specification, a computer-readable storage medium is provided that stores computer-executable instructions, which, when executed by a processor, implement the steps of the above-described spaceborne phased array antenna beam control method.

[0019] According to a sixth aspect of the embodiments of this specification, a computer program product is provided, including a computer program or instructions that, when executed by a processor, implement the steps of the above-described spaceborne phased array antenna beam control method.

[0020] One embodiment of this specification implements anti-interference from both hardware and software perspectives by determining initial array information and initial suppression information. An initial array model is constructed based on the initial array information, which includes a sidelobe suppression window function that satisfies the sidelobe earth-matching condition. The initial array excitation coefficients corresponding to the initial array model are calculated using the initial suppression information, and radiation performance information is determined. This allows for iterative optimization based on the radiation performance information, achieving a systematic and automated cyclic design of the antenna array. During the optimization process, the initial array information and initial suppression information can be continuously adjusted based on feedback from the radiation performance information to ensure that the final output target array model satisfies the sidelobe earth-matching condition. Furthermore, by calling the target array excitation coefficients, the beam of the target antenna array can be controlled, giving its radiated communication beam strong anti-interference and compatibility capabilities without requiring additional complex real-time calculations. Attached Figure Description

[0021] Figure 1 This specification provides a graph illustrating the relationship between free-space loss variation and beam tilt angle for a low-Earth orbit satellite.

[0022] Figure 2 This document illustrates a scenario demonstrating the application of sidelobe Earth matching for a low-Earth orbit satellite transmitting antenna, as provided in this specification.

[0023] Figure 3 This specification shows a low-Earth orbit satellite sidelobe Earth matching pattern.

[0024] Figure 4 A flowchart of a beam control method for a spaceborne phased array antenna according to an embodiment of this specification is shown;

[0025] Figure 5 This document illustrates a schematic diagram of a saddle-shaped sidelobe suppression window function provided in this specification.

[0026] Figure 6A A flowchart illustrating the processing procedure of a beam control method for a spaceborne phased array antenna according to an embodiment of this specification is shown.

[0027] Figure 6B This specification shows a schematic diagram of a normalized irregular array arrangement provided in one embodiment;

[0028] Figure 6C This specification shows a schematic diagram of a saddle-shaped sidelobe suppression window function curve provided in one embodiment;

[0029] Figure 6D This diagram illustrates a radiation pattern result of an initial array synthesis according to an embodiment of this specification.

[0030] Figure 6E A schematic diagram of the radiation pattern result of a final array synthesis provided in one embodiment of this specification is shown;

[0031] Figure 6F This specification shows a schematic diagram of a final irregular array arrangement provided in one embodiment;

[0032] Figure 6G This diagram illustrates the radiation pattern of a large-angle scan of an irregularly arranged array antenna according to an embodiment of this specification.

[0033] Figure 6H This diagram illustrates the radiation pattern of a large-angle scan wavefront synthesized by a regular array as provided in this specification.

[0034] Figure 7 This specification shows a schematic diagram of the structure of a satellite-borne phased array antenna beam control device according to one embodiment;

[0035] Figure 8 This specification shows a schematic diagram of the structure of a spaceborne phased array antenna beam control system according to one embodiment;

[0036] Figure 9 This is a structural block diagram of a computing device provided in one embodiment of this specification. Detailed Implementation

[0037] Many specific details are set forth in the following description to provide a full understanding of this specification. However, this specification can be implemented in many other ways than those described herein, and those skilled in the art can make similar extensions without departing from the spirit of this specification. Therefore, this specification is not limited to the specific implementations disclosed below.

[0038] The terminology used in one or more embodiments of this specification is for the purpose of describing particular embodiments only and is not intended to be limiting of the one or more embodiments of this specification. The singular forms “a,” “described,” and “the” as used in one or more embodiments of this specification and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used in one or more embodiments of this specification refers to and includes any or all possible combinations of one or more associated listed items.

[0039] It should be understood that although the terms first, second, etc., may be used to describe various information in one or more embodiments of this specification, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, first may also be referred to as second without departing from the scope of one or more embodiments of this specification, and similarly, second may also be referred to as first. Depending on the context, the word "if" as used herein may be interpreted as "when," "when," or "in response to a determination."

[0040] Furthermore, it should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in one or more embodiments of this specification are all information and data authorized by the user or fully authorized by all parties. Moreover, the collection, use and processing of related data must comply with the relevant laws, regulations and standards of the relevant countries and regions, and corresponding operation entry points are provided for users to choose to authorize or refuse.

[0041] First, the terms and concepts used in one or more embodiments of this specification will be explained.

[0042] Low Earth Orbit (LEO) satellites are satellites that operate in orbits at altitudes of approximately 160 to 2000 kilometers above the Earth's surface. It is one of the fastest-growing and most widely used types of satellites, playing a crucial role, particularly in global internet access, remote sensing, navigation enhancement, and military communications.

[0043] Antenna Array: An antenna array is a radiation system composed of multiple antenna elements (also called "array elements") arranged in a specific geometric structure. By coordinating and controlling the signal amplitude and phase of each element, an overall radiation system with specific directionality, high gain, or flexibly adjustable beam can be synthesized.

[0044] In recent years, low-Earth orbit satellite communication systems have become a research hotspot due to their potential to achieve high-speed global data coverage. As a core component of the system, spaceborne phased array antennas must simultaneously possess wide-angle scanning capability, multi-beamforming capability, and excellent sidelobe characteristics to meet the requirements of wide-area coverage, high-capacity communication, and system compatibility.

[0045] However, traditional antenna design methods face significant challenges in the unique application scenarios of low-Earth orbit satellites. (See also...) Figure 1 , Figure 1 This specification illustrates a graph showing the relationship between free-space loss variation and beam tilt angle for a low-Earth orbit satellite. Figure 1 As shown, the vertical axis represents free-space path loss, and the horizontal axis represents beam tilt angle. The curve shows that the free-space path loss between the satellite and ground changes significantly with the beam tilt angle. This leads to a core problem: when the beam scans at a large angle to the edge of the coverage area, its main lobe points to an area with high path loss, while the sidelobes may cover the nadir region with lower path loss. This difference in spatial loss cancels out the suppression gain of the antenna sidelobes, making the system susceptible to or generating interference in the nadir region. To solve this problem, this specification proposes the concept of "sidelobe-earth matching." See [link to documentation]. Figure 2 , Figure 2 This diagram illustrates a scenario where a low-Earth orbit satellite transmitting antenna sidelobe is matched to Earth, as provided in this specification. Figure 2 As demonstrated in the application scenario, an ideal antenna pattern should possess flexible sidelobe characteristics: achieving deep suppression in the nadir region (high interference risk), while allowing for more relaxed requirements at the edges of the coverage area, thus forming radiation characteristics that match the Earth's contours. See also... Figure 3 , Figure 3 This specification shows a low-Earth orbit satellite sidelobe Earth matching pattern. Figure 3 This illustrates the ideal "saddle-shaped" radiation pattern. To achieve this goal, traditional regular arrays (such as rectangular grids) are severely limited in their cell arrangement and sidelobe control freedom due to grating lobe suppression conditions (the cell spacing usually needs to be less than half a wavelength). Although irregular arrays (such as random arrays, concentric ring arrays, etc.) can overcome the grating lobe limitation and provide greater design flexibility, their radiation patterns have high background sidelobes. Traditional array synthesis algorithms have not been able to effectively solve the sidelobe shaping problem of irregular arrays, making it difficult to achieve such a complex and non-uniform sidelobe control objective.

[0046] Therefore, existing technologies lack a systematic design method that can deeply integrate the physical flexibility of irregular arrays with the specific engineering requirements of "sidelobe earth matching" and automatically output antenna design schemes with both excellent radiation characteristics and inherent anti-interference capabilities through efficient algorithms.

[0047] Based on this, this specification provides a beam control method for a spaceborne phased array antenna to solve the aforementioned technical problems. This specification also relates to a spaceborne phased array antenna beam control system, a spaceborne phased array antenna beam control device, a computing device, a computer-readable storage medium, and a computer program product, which will be described in detail in the following embodiments.

[0048] See Figure 4 , Figure 4 A flowchart of a beam control method for a spaceborne phased array antenna according to an embodiment of this specification is shown, which specifically includes the following steps.

[0049] Step 402: Determine the initial array information and initial suppression information, and construct an initial array model based on the initial array information, wherein the initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition.

[0050] Initial array information can be understood as the basic structural parameters of the array determined in the early stages of antenna design. This initial array information provides a physical basis model for subsequent pattern synthesis. Initial array information may include array type, number and arrangement of elements, element spacing, element type, operating frequency band, and bandwidth. Initial suppression information can be understood as pre-set sidelobe performance constraints to meet the sidelobe earth-matching conditions. Sidelobe suppression is not globally uniform but dynamically matched with earth geometry and propagation loss. Initial suppression information may include an angle-related upper limit for sidelobe levels (i.e., the "sidelobe suppression window"). This suppression window is constructed based on the change in free-space path loss with beam tilt angle. Stricter sidelobe suppression requirements (e.g., -35dB) are set in the nadir direction (low link loss region), while these requirements can be appropriately relaxed (e.g., -20dB) in high-loss edge regions, exhibiting non-uniform distribution characteristics such as a "saddle shape."

[0051] In practical applications, initial array information is a set of low-level parameters describing the antenna's physical structure and basic operating mode. It defines the antenna's "body" and "basic capabilities." Specifically, it can include array cell size (N), operating frequency (F), beam scan angle range (θscan), and array arrangement information. The array cell size is the total number of radiating elements in the antenna, directly affecting its gain and directivity. The operating frequency is the center frequency of the antenna, determining the wavelength of the electromagnetic wave and forming the basis for calculating all electrical dimensions (such as cell spacing). The beam scan angle range is the maximum angle by which the antenna beam can deviate from the normal direction, determining the satellite's coverage area. Array arrangement information defines the geometric layout of the antenna elements on the plane (such as regular grids, irregular concentric rings, helices, etc.). Initial suppression information is high-level information defining the antenna's smart beam performance targets. It specifies the sidelobe shape targets that the antenna's "brain" needs to achieve, specifically embodied in the "sidelobe Earth matching condition." The sidelobe Earth matching condition is the core performance indicator to be achieved by this method. It requires that when the antenna is scanning at a large angle, the sidelobe distribution of its radiation pattern can be "complementary" to the spatial path loss distribution on the Earth's surface. That is, in the nadir region where the path loss is small, the sidelobe is deeply suppressed; at the edge of the coverage area where the path loss is large, the sidelobe can be appropriately raised.

[0052] In practice, an initial array model can be constructed based on the initial array information. This initial array model can be understood as a digital antenna model generated from the initial array information, which can be used for mathematical analysis and electromagnetic simulation. Specifically, the initial array model is usually not designed from scratch. Instead, it is obtained by selecting a predefined normalized arrangement scheme (such as a normalized concentric ring array), and then scaling this normalized scheme to the actual physical dimensions using a scaling factor based on the operating frequency F and the desired average element spacing.

[0053] Furthermore, determining the initial array information and initial suppression information includes: determining array cell size information, array operation information, and array layout information, and determining the initial array information based on the array cell size information, the array operation information, and the array layout information; determining the sidelobe suppression window function, and determining the initial suppression information based on the sidelobe suppression window function.

[0054] The array element size information can be understood as the total number of radiating elements in a phased array antenna. This parameter directly determines the antenna's gain, power capacity, and beamform control accuracy, and is a fundamental structural parameter of the antenna. This information determines the antenna's physical complexity and cost basis, serving as the dimensional basis for all subsequent optimization calculations. Array operation information defines the electromagnetic environment and performance boundary conditions for antenna operation, including operating frequency and beam scanning range. Array operation information constitutes the electromagnetic constraints for antenna design. Array arrangement information describes the geometric distribution of antenna elements on the array plane. This includes regular arrangements (rectangular / triangular grids) and irregular arrangements (concentric rings, spirals, random distribution, etc.). The arrangement directly affects the antenna's radiation characteristics, especially sidelobe performance and grating lobe suppression capability.

[0055] In practical applications, the array element size N in the antenna is determined based on antenna gain, radiated power specifications, or reception quality requirements. The main design parameters for array operation information include the operating frequency F and the beam scanning angle range (maximum off-axis scanning angle θscan). Different operating frequencies affect the coordinate position of the array arrangement and, together with the beam scanning angle range, influence the maximum phase shift of the array, thus affecting the determination of the fixed-point bit width value in beam control calculations. In the array antenna arrangement scheme, regular array arrangements can be selected, such as rectangular or triangular grid arrangements, or irregular array arrangements can be chosen. Common forms include concentric ring arrays, spiral array arrangements, random point array arrangements, subarray axial rotation array arrangements, and density tapered forms of these irregular array arrangements. In the selection of array arrangement schemes, normalized array coordinate positions are provided for each arrangement scheme, forming an array arrangement scheme library.

[0056] In practical implementation, the sidelobe suppression window function defines the desired sidelobe level as a function of angle, exhibiting a "saddle-shaped" distribution pattern. Its expression is as follows:

[0057]

[0058] SLL stands for Side Lobe Level. In an antenna radiation pattern, the radiation beams in directions other than the main beam (main lobe) are called side lobes. The side lobe level represents the ratio of the radiation intensity of these side lobes to the main lobe, usually expressed in decibels (dB). This represents the desired sidelobe suppression target value (i.e., the upper limit of the sidelobe level) at the off-axis angle θ.

[0059] θ is the off-axis angle of the antenna pattern, i.e., the angle in the antenna pattern that deviates from the direction of the main beam. Its value range is typically 0 ≤ θ ≤ θmax, where θ = 0 represents the main lobe direction. θmax is the maximum off-axis angle of the sidelobe suppression window, representing the upper limit of the applicable angle range for this sidelobe suppression window. θmax < θscan because the main lobe moves during scanning, but the suppression window is usually set for a fixed angle range. n is the curve control factor, controlling the rate of change of the sidelobe suppression window curve. B is the lowest sidelobe level value at the center of the saddle shape, representing the lowest allowed sidelobe level in the region near the main lobe (where θ is smaller) (i.e., the region with the most stringent sidelobe suppression). B is a negative value, for example, -30dB means that the sidelobe at that location should be 30dB lower than the main lobe. This corresponds to the region near the nadir point, where free space loss is low, requiring even lower sidelobes to avoid interference. A is the level fluctuation value of the sidelobe suppression window, representing the total amount (in dB) that the sidelobe level is allowed to rise from θ = 0 to θ = θ_max. For example, A=9dB means that at θmax, the sidelobe level can be 9dB higher than B. This exhibits a "saddle-shaped" characteristic: strict suppression (low sidelobes) near the nadir, with appropriate relaxation allowed in the edge regions (sidelobes can be raised). See also Figure 5 , Figure 5 This diagram illustrates a saddle-shaped sidelobe suppression window function provided in this specification. The sidelobe suppression requirements for different angle regions are precisely controlled by parameters A (fluctuation value), B (center level), n (curve shape), and θmax (range of action).

[0060] In a specific embodiment of this specification, assuming a phased array antenna is designed for a Ka-band low-Earth orbit communication satellite, the array element size is determined to be 1024 radiating elements based on system link budget and gain requirements. This size ensures sufficient gain and beamforming freedom for the antenna. The array operation information is determined as follows: operating frequency: set to 30 GHz (wavelength λ = 1 cm); beam scanning range: ±60° based on satellite coverage requirements. These parameters provide the basis for subsequent wavelength normalization and scanning performance optimization. The array layout information is determined by selecting an irregular spiral layout from a predefined array scheme library. This layout has a natural gradient, which is beneficial for achieving a specific sidelobe distribution. A sidelobe suppression window function is constructed, and saddle-shaped function parameters are set. According to this function, the sidelobe is below -32 dB at the nadir (θ = 0°), and can be relaxed to -22 dB at 50°.

[0061] Based on this, the complex antenna design problem is decomposed into three clearly defined information modules: scale, operation, and layout. Standardized design input specifications are established to achieve modularization and systematization of design parameters. A parameterized saddle-shaped function is used to define the sidelobe suppression requirement, transforming the fuzzy concept of "Earth matching" into a precise mathematical optimization objective, providing a clear convergence criterion for subsequent algorithm optimization.

[0062] Furthermore, constructing an initial array model based on the initial array information includes: determining initial array coordinate information based on the array arrangement information, and determining coordinate adjustment parameters based on the array operation information; adjusting the initial array coordinate information using the coordinate adjustment parameters to obtain target array coordinate information; and constructing an initial array model based on the target array coordinate information.

[0063] The initial array coordinate information can be understood as a set of normalized coordinates obtained from a predefined array layout scheme library. These coordinates describe the relative positional relationships of the antenna elements, but have not yet been mapped to specific physical dimensions. The coordinate adjustment parameters can be understood as scaling factors determined based on the operating frequency and the desired element spacing, used to convert the normalized coordinates into actual physical coordinates. The scaling factor is the bridge connecting electromagnetic performance and physical implementation; the calculation formula is typically: scale = k × λ, where λ is the operating wavelength and k is a coefficient related to the desired spacing. The target array coordinate information can be understood as the actual physical coordinates obtained after converting the normalized initial coordinates through the scaling factor, directly corresponding to the element positioning during antenna manufacturing. These coordinates determine the actual aperture size and element density of the antenna, directly affecting its radiation characteristics. The initial array model is a digital antenna geometric model established based on the target array coordinate information, which can be used for electromagnetic simulation and performance analysis. This model fully describes the physical structure of the antenna and is the foundation for subsequent array synthesis and performance evaluation.

[0064] In practical applications, the array layout information provides normalized array coordinates. Multiplying these normalized array coordinates by a scaling factor (scale) yields the coordinates of array elements within the specific hardware phased array. Changing the scaling factor (scale) controls the average element spacing. The specific value of the scaling factor (scale) is influenced by the antenna operating frequency and the desired average element spacing; the higher the antenna operating frequency, the smaller the value, while the larger the desired average element spacing, the larger the value. Due to the introduction of irregular array layouts, there is a larger range of values ​​to choose from compared to regular array layouts. The maximum value of the scaling factor (scale) is greater than, rather than less than, the following function:

[0065]

[0066] Where c is the speed of light, F is the antenna operating frequency, and θscan is the maximum off-axis angle of beam scanning. The above function represents the traditional theoretical boundary condition for avoiding grating lobes, while the method provided in this specification breaks through this traditional limitation. Specifically, this function formula is a classic criterion in phased array antenna design, used to ensure that the antenna does not generate grating lobes during scanning. The periodic structure of traditional regular arrays is the root cause of grating lobe generation. However, the irregular array arrangement in the embodiments of this specification breaks the periodicity of the array, making the positions of the antenna elements irregular. This "disorder" fundamentally disrupts the condition for stable in-phase superposition of path differences, thus effectively suppressing or even eliminating grating lobes. Because the limitation of grating lobes is overcome, a larger average element spacing can be selected when designing the antenna. With a fixed total number of elements (N), a larger spacing means that the physical aperture (size) of the antenna can be made larger. While meeting the same performance requirements, fewer antenna elements can be used (due to sparseness), or better performance can be achieved with the same number of elements, which is beneficial for reducing the weight, power consumption, and cost of spaceborne equipment. Furthermore, the irregular array scheme, combined with the beam control method of the spaceborne phased array antenna, can more effectively approximate the sidelobe suppression window by increasing rather than decreasing the average array spacing, thus achieving a more efficient approximation of the Earth-matched sidelobe suppression window. This not only fully leverages the advantages of irregular arrays in terms of arrangement and aperture expansion, but also precisely manages the residual radiation energy that may result from the large spacing and irregularity through beam control, achieving a complementary effect between the two.

[0067] In a specific embodiment of this specification, determining the initial array coordinate information includes selecting a "concentric ring irregular arrangement" scheme from the array arrangement scheme library and obtaining the normalized coordinate set of this scheme, where the minimum cell spacing is normalized to 1. This normalized coordinate describes the relative positional relationship between cells but does not involve specific dimensions. Determining the coordinate adjustment parameters includes calculating a scaling factor based on the operating frequency F=30GHz (wavelength λ=1cm) in the array operation information, aiming to obtain a design with an average cell spacing ≈0.75λ: scale=0.75×λ=0.75cm. This parameter ensures that the final array meets electrical performance requirements while avoiding grating lobes. Adjusting the initial array coordinate information using the coordinate adjustment parameters includes performing a coordinate transformation: physical coordinate = normalized coordinate × scale. For example, normalized coordinates (1,0) are converted to physical coordinates (0.75cm,0cm), generating a target coordinate set containing the precise physical positions of all 1024 cells. The initial array model construction includes establishing a digitized array geometric model based on target coordinate information. This model can be directly imported into electromagnetic simulation software for performance analysis, providing an accurate physical basis for subsequent excitation coefficient optimization. By combining irregular arrays with spaceborne phased array antenna beam control methods, it is possible to better approximate sidelobe Earth matching and maximize the technical advantages and design freedom of irregular arrays while controlling the residual energy after grating lobe suppression. Irregular array technology provides greater application freedom for spaceborne phased array antenna beam control methods, while spaceborne phased array antenna beam control methods compensate for the shortcomings of irregular arrays in controlling the residual energy distribution under grating lobe suppression.

[0068] Based on this, by using a "normalized coordinate library + scaling factor" approach, array design is transformed from an experience-based manual operation into a repeatable automated process, achieving standardization and automation of the design process. The introduction of the scaling factor allows for flexible exploration of the impact of different cell spacings on performance without altering the basic arrangement rules, providing crucial degrees of freedom for optimizing sidelobe characteristics and grating lobe suppression. Accurate calculation of the scaling factor based on the operating frequency ensures a strict match between the array's electrical and physical dimensions, preventing performance deviations caused by size mismatches from the outset.

[0069] Step 404: Calculate the initial array excitation coefficients corresponding to the initial array model using the initial suppression information, and determine the radiation performance information of the initial array model using the initial array excitation coefficients.

[0070] The initial array excitation coefficients can be understood as complex weight vectors calculated through array synthesis algorithms, containing the amplitude and phase information required for each antenna element. These coefficients serve as a bridge between the array geometry and radiation performance, directly determining the beam shape and direction. Radiation performance information can be understood as the quantitative results obtained from electromagnetic simulation analysis of the array model after applying the excitation coefficients. This mainly includes key performance indicators such as radiation pattern characteristics, sidelobe distribution, and the approximation degree of the suppression window, used to objectively evaluate whether the current design meets the requirements.

[0071] In practical applications, the engineering requirements of the suppression window are transformed into mathematical constraints for algorithm optimization. The optimal excitation coefficients are intelligently solved using the Second-Order Cone Programming (SOCP) convex optimization method. The SOCP method can express the main lobe gain constraint as a linear equation and the level suppression requirements for multiple sidelobe regions as second-order cone inequalities. It achieves optimal beamforming by minimizing the norm of the array weighting vector, thus more flexibly and accurately approximating the complex "saddle-shaped" sidelobe suppression window. Furthermore, precise electromagnetic simulation is used to quantitatively evaluate the actual radiation performance, establishing a complete technical chain from design objectives to performance verification. This enables automated, quantitative evaluation, and closed-loop optimization of antenna design, significantly improving design efficiency and result reliability, and providing accurate decision-making basis for subsequent iterative optimization.

[0072] Furthermore, calculating the initial array excitation coefficients corresponding to the initial array model using the initial suppression information includes: determining the beam pointing information corresponding to the initial array model; calculating beam steering vector information based on the beam pointing information and the target array coordinate information; and calculating the initial array excitation coefficients corresponding to the initial array model based on the beam steering vector information and the sidelobe suppression window function in the initial suppression information.

[0073] The beam pointing information can be understood as the desired main lobe radiation direction, usually represented by the off-axis angle θ. This is the target angle that the beam needs to point precisely to, determining the direction of communication link establishment. The beam steering vector information can be understood as a complex vector describing the phase relationship of the electromagnetic wave as it reaches each element of the array from the desired beam direction. Each element corresponds to an antenna element, ensuring that the radiated signals of all elements in the target direction are superimposed in phase. The sidelobe suppression window function defines the sidelobe suppression level requirement that varies with the angle; its specific form is a saddle-shaped function, used to achieve sidelobe earth matching. Based on this function, multiple sidelobe angle regions that need to be suppressed and their corresponding maximum allowable sidelobe levels can be determined. This information will be directly used to construct the constraints of the optimization problem.

[0074] In practical applications, the design parameter settings determine the beam pointing angle towards the target, the operating frequency, the antenna element positions, and the sidelobe suppression window function. The beam pointing information is determined based on this pointing angle. The beam steering vector information is calculated based on the target pointing angle, operating frequency, and array arrangement. Using the sidelobe suppression window function, discrete sidelobe suppression angles and their corresponding suppression levels are extracted; this information is directly used to construct the constraints for the optimization problem.

[0075] In practical implementation, the array excitation coefficients can be calculated using second-order cone programming (SOCP). This method, under the constraint of ensuring the main lobe of the beam accurately points towards the target direction, constructs the complex sidelobe level requirements, which vary with angle and are specified by the "sidelobe earth-matching" suppression window function, into a series of second-order cone inequalities. Solving this convex optimization problem yields the corresponding array antenna excitation coefficients, i.e., the complex weight values ​​of each element. Compared to traditional methods, SOCP can directly and accurately treat the non-uniform sidelobe suppression target as a constraint, guaranteeing a globally optimal solution. Subsequently, the intelligent beam control system for the array antenna sends the solved array antenna excitation coefficients to the antenna RF system based on the address bits to control the array antenna's radiated beam.

[0076] In a specific embodiment of this specification, taking a 512-element phased array in the Ku band as an example, with a beam pointing angle of 45°, the beam pointing information is determined to be 45°. A complex beam steering vector of length 512 is calculated based on the beam pointing and the physical coordinates of the 512 elements. The saddle-shaped suppression window function is analyzed, and multiple discrete angles are selected in the sidelobe region requiring suppression. The suppression level corresponding to each angle is determined, thus constructing the SOCP problem. The main lobe pointing constraint is achieved by the equality constraint formed by the beam steering vector, while the sidelobe suppression constraint is achieved by the second-order cone inequality constraint at each discrete angle. The problem is solved using second-order cone programming (SOCP), outputting the 512-dimensional initial array excitation coefficients (complex numbers).

[0077] Based on this, by directly transforming the main lobe pointing requirement and the sidelobe suppression window function into constraints of a convex optimization problem, and solving it using a second-order cone programming method, precise control of the beam pattern is achieved. This method not only ensures the precise pointing of the main lobe but also strictly shapes the sidelobe shape to meet the Earth-matching requirements of the sidelobe. It provides a systematic calculation method for generating the optimal excitation coefficients that meet specific radiation characteristics, effectively improving the accuracy and efficiency of array synthesis.

[0078] Furthermore, based on the sidelobe suppression window function in the beam steering vector information and the initial suppression information, the initial array excitation coefficients corresponding to the initial array model are calculated, including: constructing a second-order cone programming problem based on the beam steering vector information and the sidelobe suppression window function; and calculating the initial array excitation coefficients corresponding to the initial array model according to the second-order cone programming problem.

[0079] The second-order cone programming problem is a convex optimization problem, whose standard form includes an objective function, equality constraints, and inequality constraints. The objective function is typically set to minimize the norm of the array weighting vector (i.e., minimize the total radiated power), which helps to find the most "economical" excitation scheme while meeting performance requirements. The equality constraints are determined by the beam steering vector information and are used to ensure that the main lobe has unity gain (i.e., distortion-free pointing) at the target pointing angle. The inequality constraints are determined by the sidelobe suppression window function, which transforms the complex sidelobe suppression level, which continuously varies with angle and is required for "sidelobe earth matching," into a series of upper amplitude constraints at discrete angles, mathematically in the form of second-order cone constraints.

[0080] In practical applications, the optimization problem is constructed as follows: First, the beam steering vector is calculated based on the target beam pointing angle, and equality constraints are established accordingly; second, based on the requirement of "sidelobe earth matching", multiple discrete angles and their corresponding maximum allowable sidelobe levels are sampled from the sidelobe suppression window function, and a set of second-order cone inequality constraints are established accordingly; finally, the 2-norm square of the array weighted vector (i.e., the excitation coefficient vector) is minimized as the objective function.

[0081] In a specific embodiment of this specification, referring to the above example, the problem of constructing the input beam steering vector (45° direction) and the sidelobe suppression window function is described. Specifically, corresponding level constraints are set in the sidelobe region that needs to be controlled (e.g., selecting an angle at regular intervals from 0° to 55°). This problem is constructed as a SOCP problem and a dedicated solver is called to calculate it, obtaining a 512-dimensional optimal excitation coefficient vector.

[0082] Based on this, a direct and accurate mathematical optimization framework was established by directly modeling the complex beamforming shape requirements as constraints of a convex optimization problem and solving it using the second-order cone programming (SOCP) method. This method transforms the beamforming problem into a deterministic optimization problem, ensuring that while precisely controlling the main lobe pointing direction, the sidelobe shape can be strictly shaped to conform to the "sidelobe Earth matching" condition. This provides a reliable theoretical guarantee and efficient computational means for obtaining antenna design schemes that combine excellent radiation characteristics and inherent anti-interference capabilities.

[0083] Furthermore, based on the beam steering vector information and the sidelobe suppression window function in the initial suppression information, a second-order cone programming problem is constructed, including: determining equality constraint information based on the beam steering vector information, determining inequality constraint information based on the sidelobe suppression window function; and constructing a second-order cone programming problem based on the equality constraint information and the inequality constraint information.

[0084] The second-order cone programming problem is a convex optimization problem. It aims to minimize the norm of the array weighted vector, using the main lobe pointing gain as an equality constraint and the level limits of multiple sidelobe regions as inequality constraints. The equality constraint, which guarantees the accurate pointing of the main lobe, is represented by the dot product of the beam steering vector and the array weighted vector being equal to 1. The inequality constraint, derived from the sidelobe suppression window function, is used to achieve the "sidelobe earth-matching" characteristic. Its form is that the absolute value of the dot product of the beam steering vector and the array weighted vector is no greater than the suppression level value corresponding to that angle. This type of inequality constraint can be represented as a second-order cone constraint.

[0085] In a specific embodiment of this specification, a second-order cone programming problem is constructed based on the beam steering vector information and the sidelobe suppression window function. Specifically, this includes: setting the gain constraint for the main lobe pointing angle (e.g., 45° direction) as an equality constraint; setting corresponding level suppression inequality constraints for discrete sidelobe angles according to the sidelobe suppression window function; and using the minimization of the 2-norm square of the array weighted vector as the objective function. A second-order cone programming solver is used to solve this optimization problem, and the optimal weight vector obtained is used as the excitation coefficient. Subsequently, it can be verified whether these coefficients meet the design requirements, such as main lobe pointing: gain of 0dB (no distortion) in the 45° direction, and sidelobe characteristics: the level in each suppression region meets the requirements of the saddle-shaped window. The final output is a complex excitation coefficient vector of length 512.

[0086] Based on this, by directly transforming the engineering requirement of "sidelobe Earth matching" into the constraints of a convex optimization problem, and by performing rigorous mathematical optimization based on the second-order cone programming method, precise control of the complex radiation pattern shape was achieved. This not only ensured the accurate pointing of the main lobe and the distortion-free transmission of the signal, but also enabled intelligent shaping of the sidelobe shape by directly using the sidelobe suppression window function as a constraint. This provides a key technical guarantee for reliable communication of spaceborne phased array antennas in strong interference environments.

[0087] Furthermore, determining the radiation performance information of the initial array model through the initial array excitation coefficient includes: loading the initial array excitation coefficient through the initial array model to obtain the radiation pattern corresponding to the initial array model; determining the radiation pattern information corresponding to the radiation pattern, and calculating the quantization index information of the initial array model based on the radiation pattern information and the initial suppression information; comparing the quantization index information with preset index information to obtain the radiation performance information of the initial array model.

[0088] The radiation pattern can be understood as the three-dimensional spatial radiation field distribution calculated by electromagnetic simulation software, visually displaying the antenna's radiation intensity in different directions, including key feature information such as the main lobe and side lobes. The pattern information can be understood as structured data extracted from the radiation pattern, including normalized pattern data for a specific cross-section, side lobe level values, beamwidth, and other key parameters. Quantitative index information can be understood as performance evaluation values ​​obtained through mathematical calculations, used to objectively measure the degree of fit between the actual radiation pattern and the target suppression window, mainly including statistical indicators such as root mean square error and maximum deviation. Preset index information can be understood as pre-set performance qualification thresholds, such as maximum permissible deviation and minimum root mean square error requirements, serving as objective standards for judging whether the design meets the requirements.

[0089] In practical applications, the obtained array excitation coefficients can be quantized according to the phased array hardware capabilities, mainly through phase quantization and amplitude quantization, so that the quantized array excitation coefficients match the amplitude and phase errors of the phased array hardware capabilities. Beam performance evaluation of the array model is then performed based on the initial array excitation coefficients. The radiation beam performance of the initial array model at the operating frequency F and after quantizing the array excitation coefficients is analyzed, calculated, and evaluated. Generally, radiation beam performance is evaluated by normalizing the radiation beam pattern. If the normalized radiation beam pattern of the current array has sidelobe Earth-matching characteristics and the sidelobe distribution matches the sidelobe suppression window, then the process proceeds to first saving and outputting the full array position data. If the sidelobe distribution of the current array radiation beam is abnormal or the approximation is insufficient, then the process jumps to the array cyclic update process.

[0090] In a specific embodiment of this specification, the aforementioned calculated 512-dimensional excitation coefficients are loaded into the array electromagnetic model, and a three-dimensional radiation pattern is calculated using full-wave electromagnetic simulation software. The radiation characteristics at a 45° beam pointing angle are analyzed in detail, generating a complete radiation pattern dataset containing amplitude and phase information. Normalized radiation pattern data is extracted, and sidelobe levels are sampled at 1° intervals within the range of 0° to 55°. Key quantization indicators, including root mean square error (RMSE), maximum positive deviation, and sidelobe matching degree, are calculated. The calculated quantization indicators are compared with preset indicators, such as an RMSE greater than a preset threshold or a maximum positive deviation greater than a preset threshold. Radiation performance information is generated based on the comparison results. This radiation performance information may include the calculated quantization indicators, the results of whether the array model meets the standards, and the reasons for any non-compliance.

[0091] Based on this, a data-based performance evaluation system was established by obtaining radiation patterns through precise electromagnetic simulation and using quantitative indicators to objectively evaluate their conformity with the target suppression window. This system transformed subjective experience-based judgment into objective quantitative analysis, providing clear improvement directions and convergence criteria for subsequent iterative optimization and significantly improving the scientific nature and efficiency of antenna design.

[0092] Step 406: Iteratively optimize the initial array information and the initial suppression information based on the radiation performance information until a target array model that satisfies the sidelobe earth matching condition and the target array excitation coefficients of the target array model are obtained. The target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array.

[0093] The radiation performance information includes comprehensive data from quantitative evaluation results, such as root mean square error (RMSE) and maximum deviation (Δ_max), objectively reflecting the gap between the current array design performance and the target requirements. Therefore, based on the radiation performance information, it can be determined whether the current array model meets the requirements. If not, the initial array information and initial suppression information can be readjusted until an array model that satisfies the sidelobe earth-matching condition and its corresponding array excitation coefficients are obtained. The target array model is the final array geometry determined after multiple rounds of optimization, including information required for manufacturing such as element arrangement and physical coordinates. The target array excitation coefficients are the optimal set of excitation weights that match the target array model, ensuring that the antenna achieves the expected radiation characteristics during operation.

[0094] In practical applications, iterative optimization is a closed-loop optimization process based on performance feedback. By systematically adjusting key parameters and recalculating them, the design performance gradually approaches the target requirements.

[0095] Furthermore, iterative optimization of the initial array information and the initial suppression information based on the radiation performance information includes: if, according to the radiation performance information, the initial array model does not meet the sidelobe Earth matching condition, adjusting the initial array information and the initial suppression information to obtain intermediate array information and intermediate suppression information; using the intermediate array information as the initial array information and the intermediate suppression information as the initial suppression information; and continuing to construct the initial array model based on the initial array information; if, according to the radiation performance information, the initial array model meets the sidelobe Earth matching condition, using the initial array model corresponding to the initial array information as the target array model, and using the initial array excitation coefficient of the initial array model as the target array excitation coefficient.

[0096] In practical applications, the initial array information and initial suppression information can be adjusted during the array cyclic update process. For example, the average cell spacing can be readjusted, and the sidelobe suppression window setting, array synthesis optimization iteration and output, and array excitation coefficient quantization and setting can be performed sequentially to complete the update of the entire array. Then, the beam performance of the array model is evaluated. This cycle continues until the sidelobe distribution of the radiated beam of the updated array model approaches the sidelobe suppression window. At this point, the cycle is exited, and the data saving and output operations of the array position and excitation coefficients are performed.

[0097] If the sidelobe Earth matching condition is not met, the initial array information and initial suppression information can be adjusted to obtain intermediate array information and intermediate suppression information. The intermediate array information is the set of transitional array parameters generated during the iteration process, including adjusted array size, operating frequency, scanning range, or arrangement. The intermediate suppression information is the transitional suppression parameters generated during the iteration process, typically manifested as adjusted saddle-shaped suppression window function parameters. The intermediate array information is then used as the initial array information, and the intermediate suppression information is used as the initial suppression information. The process then proceeds to the next iteration, re-executing steps such as building the initial array model and calculating the initial array excitation coefficients. Finally, the array model of the current iteration is evaluated again, and based on the comparison between the quantized indicators in the radiation performance information and preset thresholds, it automatically determines whether to continue iterating or terminate the optimization. If the sidelobe Earth matching condition is met, the iterative optimization loop can be terminated. The initial array model generated in the current iteration is used as the target array model, and the initial array excitation coefficients are used as the target array excitation coefficients.

[0098] In a specific embodiment of this specification, after performance evaluation reveals non-compliance, intermediate information is generated through parameter adjustments. For example, intermediate array information adjustments include changing the scaling factor from 0.7λ to 0.75λ, while maintaining the operating frequency and scanning range unchanged. Intermediate suppression information adjustments include changing the fluctuation value A from 10dB to 11dB and the curve factor n from 1 to 0.8. The intermediate array information and the intermediate suppression information are used as new initial array information and new initial suppression information, respectively, and the model construction, coefficient calculation, and performance evaluation process is re-executed. After three iterations, based on the radiation performance information, the array model is determined to meet the sidelobe Earth matching condition. The output includes the target array model (current initial array model, result of the third round of optimization) and the target array excitation coefficients (current initial array excitation coefficients, result of the third round of calculation). The iteration loop terminates, and the optimal design scheme suitable for engineering implementation is output.

[0099] Based on this, by establishing a clear condition judgment and parameter update mechanism, intelligent decision-making and automatic flow of the design optimization process are realized, transforming the traditional iterative process that relies on manual judgment into a systematic and standardized automatic process. This not only significantly improves optimization efficiency, but also ensures the performance reliability of the final design results through strict convergence criteria.

[0100] Furthermore, the method also includes: designing the target antenna array according to the target array model; and performing beam control through the target antenna array according to the target array excitation coefficient.

[0101] The target antenna array can be understood as an antenna system actually manufactured based on the geometric parameters and physical specifications of the target array model, including hardware components such as array elements, feed networks, phase shifters, and attenuators. Beam control is the process by which the beam control system, while the satellite is in orbit, calls and applies the target array excitation coefficients in real time according to communication requirements, driving the antenna to generate a radiation beam with a specific direction and shape.

[0102] In practical applications, designing a target antenna array based on a target array model is the process of converting the digitized optimization results into manufacturable engineering drawings and process documents. Specifically, it may include steps such as precise unit positioning, feed network layout, and structural support design.

[0103] In a specific embodiment of this specification, machining drawings are generated based on the unit coordinate data in the target array model, a radome drilling positioning diagram is designed, the installation scheme of the packaged antenna module is determined according to the unit spacing, and a corresponding RF feed network is designed to ensure signal distribution to each unit. Phase shifters and attenuator arrays are configured. A beam control interface circuit is designed to support rapid loading and switching of excitation coefficients. During subsequent satellite operation in orbit, the satellite beam control computer stores an excitation coefficient lookup table containing target excitation coefficients corresponding to different beam directions. When a communication link with the ground station needs to be established, the beam pointing angle is determined, the corresponding excitation coefficient is retrieved from the lookup table, and the coefficient is decomposed into amplitude and phase commands, which are sent to the attenuators and phase shifters of each channel. Each antenna unit radiates electromagnetic waves of specific amplitude and phase according to the commands, which are then interferometrically superimposed in space to form a directional beam. Simultaneously, sidelobe Earth-matching characteristics are automatically achieved, resulting in deep suppression in the nadir region.

[0104] Based on this, the digital results of the aforementioned optimization design phase are fully integrated into engineering manufacturing and on-orbit application. Precision manufacturing based on the target array model ensures the inherent performance advantages of the antenna hardware. Furthermore, real-time loading of the target excitation coefficient enables the satellite to automatically and accurately form an intelligent beam with both excellent directivity and strong anti-interference capabilities during operation. Ultimately, a complete value loop from optimization algorithm to engineering effectiveness is achieved, providing a reliable and intelligent antenna solution for low-orbit satellite communication systems.

[0105] This specification provides a beam control method for a spaceborne phased array antenna, comprising: determining initial array information and initial suppression information; constructing an initial array model based on the initial array information, wherein the initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition; calculating the initial array excitation coefficients corresponding to the initial array model using the initial suppression information, and determining the radiation performance information of the initial array model using the initial array excitation coefficients; iteratively optimizing the initial array information and the initial suppression information based on the radiation performance information until a target array model satisfying the sidelobe Earth matching condition and the target array excitation coefficients of the target array model are obtained, wherein the target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array. This method achieves anti-interference from both hardware and software perspectives by determining the initial array information and initial suppression information. It constructs an initial array model based on the initial array information, and satisfies the sidelobe Earth matching condition using the initial suppression information. It calculates the initial array excitation coefficients corresponding to the initial array model using the initial suppression information and determines the radiation performance information, enabling iterative optimization based on the radiation performance information, and realizing a systematic and automated cyclic design of the antenna array. During the optimization process, the initial array information and initial suppression information can be continuously adjusted based on the feedback of radiation performance information to ensure that the final output target array model meets the sidelobe earth matching condition. Furthermore, by calling the target array excitation coefficient, the beam of the target antenna array can be controlled, enabling its radiated communication beam to have strong anti-interference and compatibility capabilities without the need for additional real-time complex calculations.

[0106] The following is in conjunction with the appendix Figure 6A Taking the application of the satellite-borne phased array antenna beam control method provided in this specification in antenna design as an example, the beam control method of the satellite-borne phased array antenna will be further explained. Among them, Figure 6A The present specification shows a flowchart of a beam control method for a spaceborne phased array antenna according to an embodiment of the present specification, which specifically includes the following steps.

[0107] Step 602: Determine the array cell size information, array operation information, and array layout information, and determine the initial array information based on the array cell size information, array operation information, and array layout information.

[0108] In one feasible approach, a Ka-band low-Earth orbit communication satellite requires the design of a phased array antenna with sidelobe Earth-matching characteristics, operating at a frequency of 17.7-20.2 GHz. It must achieve a beam scanning capability of ±56° and possess excellent anti-interference performance during large-angle scanning. Initial array information is determined, including array element size: based on antenna gain specifications, the array size is determined to be 604 elements; array operation information: operating frequency F = 20.2 GHz, beam scanning range θscan = 56°; and array layout information: a non-irregular concentric ring array arrangement of AiP modules is selected from the array layout scheme library. (See also...) Figure 6B , Figure 6B This specification illustrates a normalized irregular array arrangement according to an embodiment. Each AiP module contains four equally spaced antenna elements. This yields the normalized array coordinates of the irregular arrangement (minimum spacing is 1m).

[0109] Step 604: Determine the sidelobe suppression window function, and determine the initial suppression information based on the sidelobe suppression window function.

[0110] In one feasible implementation, the saddle-shaped sidelobe suppression window function is defined as: SLL_wind(θ) = 9 × [1 - (cos(0.5π × θ / 60))^1] - 30 (dB). See also Figure 6C , Figure 6C This specification shows a schematic diagram of a saddle-shaped sidelobe suppression window function curve according to an embodiment of the present specification. Figure 6C The image shows a comparison of the saddle-shaped suppression window shape under different parameter settings. In this embodiment, the parameters for the saddle-shaped sidelobe suppression window are determined as follows: A=9dB (fluctuation value), B=-30dB (center level), n=1 (curve factor), θmax=60°.

[0111] Step 606: Determine the initial array coordinate information based on the array layout information, and determine the coordinate adjustment parameters based on the array operation information. Adjust the initial array coordinate information using the coordinate adjustment parameters to obtain the target array coordinate information, and construct the initial array model based on the target array coordinate information.

[0112] In one feasible approach, the normalized coordinate information of the concentric ring array is obtained, the scaling factor is set to scale=0.5×c / F (c is the speed of light), the half-wavelength unit spacing is obtained, the target array coordinate information is generated, and a complete initial array model is constructed.

[0113] Step 608: Determine the beam pointing information corresponding to the initial array model, and calculate the beam steering vector information based on the beam pointing information and the target array coordinate information.

[0114] In one feasible approach, the beam pointing direction is set to θ_main=56°, and the beam steering vector is calculated.

[0115] Step 610: Calculate the initial array excitation coefficients corresponding to the initial array model based on the sidelobe suppression window function in the beam steering vector information and initial suppression information.

[0116] In one feasible approach, equality constraint information is determined based on beam steering vector information, inequality constraint information is determined based on sidelobe suppression window function, a second-order cone programming problem is constructed based on equality constraint information and inequality constraint information, and the initial array excitation coefficients corresponding to the initial array model are calculated based on the second-order cone programming problem.

[0117] Step 612: Load the initial array excitation coefficients through the initial array model to obtain the radiation pattern corresponding to the initial array model, determine the radiation pattern information corresponding to the radiation pattern, and calculate the quantization index information of the initial array model based on the radiation pattern information and the initial suppression information. Compare the quantization index information with the preset index information to obtain the radiation performance information of the initial array model.

[0118] In one feasible approach, excitation coefficients are loaded into the array model, and electromagnetic simulation is performed to obtain the radiation pattern.

[0119] Step 614: Iteratively optimize the initial array information and initial suppression information based on radiation performance information.

[0120] In one feasible approach, radiation pattern data is extracted, and the array excitation system is quantized based on the hardware capability of a 5-bit phase-shifted attenuation phased array. The phase quantization error is 11.25°, and the amplitude quantization error is 0.5 dB. The quantized array excitation system is then used to evaluate the beam performance in the array analysis model. The normalized radiation pattern of the radiated beam is used for radiation beam performance evaluation. The obtained normalized radiation pattern of the array beam exhibits certain sidelobe Earth-matching characteristics. See [link to relevant documentation]. Figure 6D , Figure 6D This specification shows a schematic diagram of the radiation pattern result of an initial array synthesis according to an embodiment of the present specification. Figure 6DIt can be seen that compared with the original radiation pattern (dashed line) without array synthesis optimization, the sidelobes near the nadir point are suppressed, but the earth-matching characteristics of the sidelobes are not significant enough, and the level in the region near the nadir point is not significantly improved compared with the region far from the sidelobes. Therefore, it is determined that the initial array model does not meet the earth-matching conditions for sidelobes. The initial array information and initial suppression information are adjusted to obtain intermediate array information and intermediate suppression information. The intermediate array information is used as the initial array information, and the intermediate suppression information is used as the initial suppression information. The initial array model is then constructed based on the initial array information. After the array is updated, the beam performance of the array application model is evaluated. This process is repeated until the scaling factor is set to scale=0.75×c / F and A is set to 12, B to -35, and n to 0.5 in the sidelobe suppression window settings. When the sidelobe distribution of the updated array application model's radiation beam approaches the sidelobe suppression window, the loop is exited, and the array position data and excitation coefficients are saved and output. See [link to relevant documentation] Figure 6E , Figure 6E This specification shows a schematic diagram of the radiation pattern result of a final array synthesis according to an embodiment of the present specification. Figure 6E As can be seen, compared with the original radiation pattern (dashed line), the sidelobes near the nadir point are significantly suppressed, and the voltage level in the region near the nadir point is significantly lower than that in the region far from the sidelobes, thus achieving the sidelobe earth-matching characteristic of the array antenna.

[0121] Step 616: Design the target antenna array based on the target array model, and perform beam control through the target antenna array according to the target array excitation coefficient.

[0122] In one feasible implementation, antenna panels are fabricated and 604 AiP antenna modules are installed based on the coordinate data of the target array model. The excitation coefficients of the target array are programmed into a lookup table in the satellite carrier control computer. During satellite operation, the corresponding beam pointing excitation coefficients are called according to communication requirements to form a smart beam with both precise pointing and anti-interference capabilities in real time. To verify the effectiveness of the satellite-borne phased array antenna beam control method provided in this specification, based on the parameters described in the specific embodiments, a complete modeling, synthesis, and performance analysis simulation was performed using the simulation software MATLAB. The method used in the embodiments of this specification (using an irregular array) was compared with the traditional regular array method under the same key system indicators. See also Figure 6F , Figure 6F This specification shows a schematic diagram of a final irregular array arrangement provided in one embodiment. Figure 6F As shown, this irregular array arrangement contains 604 elements, with a minimum element spacing of 0.75 times the wavelength (λ). Applying a smart beam control algorithm to this array yields a radiation pattern at a large-angle scanning beamwidth (beam pointing at 56°). See [link / reference]. Figure 6G , Figure 6G This specification shows a schematic diagram of the radiation pattern of a large-angle scanning beam pattern of an irregular array antenna according to an embodiment of the present specification. According to the radiation pattern, the irregular array antenna can achieve beam scanning at an angle of ±56° without grating lobes, and the side lobes have earth matching, thus achieving a good intelligent beam control effect.

[0123] The simulation results above demonstrate that the method provided in this specification can quickly and efficiently generate intelligent beam control for irregularly arranged antenna arrays. It also exhibits large-angle scanning wavefront sidelobe earth matching effects for irregular array arrangements with a spacing greater than half a wavelength, achieving uniform array element arrangement within the aperture and demonstrating good engineering feasibility. Furthermore, the irregular array arrangement generated in this specification possesses a large minimum array spacing characteristic, overcoming the limitations of grating lobe suppression under rectangular regular arrays (the element spacing in this embodiment is required to be less than 0.55λ), thus granting phased array antennas more flexible design capabilities under this intelligent beam control system. See also... Figure 6H , Figure 6H This specification shows a schematic diagram of the radiation pattern result of a large-angle scan wavefront synthesis of a regular array, based on the information provided in this specification. Figure 6H As shown in the figure, the radiation pattern of a large-angle scan beam obtained after sidelobe suppression array synthesis of a regular array (rectangular grid spacing of 0.75λ) is presented. It can be observed that the regular array generates grating lobes at large spacing, affecting interference suppression and link sidelobe matching. Therefore, the traditional regular array arrangement limits the use of intelligent beam control and lacks sufficient numerical space for setting the average element spacing. This also means that the traditional phased array antenna intelligent beam control system does not possess the core technical point of "average element spacing setting" found in the spaceborne phased array antenna beam control method of this specification.

[0124] This specification provides a beam control method for a spaceborne phased array antenna. In this embodiment, a Ka-band spaceborne phased array antenna was successfully designed and manufactured. When scanning at a large angle of 56°, the antenna achieves a deep suppression of the sidelobes of its radiation pattern near the nadir point, reaching -35dB, while the suppression is moderately broadened to -23dB at the edge of the coverage area. This perfectly realizes the "sidelobe Earth matching" characteristic, significantly improving the anti-interference capability and spectrum compatibility of the satellite communication system. The entire design process, from parameter setting to final optimization, requires only a few iterations, demonstrating the efficiency and engineering practicality of the spaceborne phased array antenna beam control method.

[0125] Corresponding to the above method embodiments, this specification also provides embodiments of a spaceborne phased array antenna beam control device. Figure 7 This specification illustrates a schematic diagram of a beam control device for a spaceborne phased array antenna according to one embodiment. Figure 7As shown, the device includes:

[0126] The determination module 702 is configured to determine initial array information and initial suppression information, and to construct an initial array model based on the initial array information, wherein the initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition;

[0127] The calculation module 704 is configured to calculate the initial array excitation coefficients corresponding to the initial array model using the initial suppression information, and to determine the radiation performance information of the initial array model using the initial array excitation coefficients;

[0128] The optimization module 706 is configured to iteratively optimize the initial array information and the initial suppression information based on the radiation performance information until a target array model that satisfies the sidelobe earth matching condition and the target array excitation coefficients of the target array model are obtained. The target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array.

[0129] Optionally, the determining module 702 is further configured to determine array cell size information, array operation information, and array layout information, and determine initial array information based on the array cell size information, the array operation information, and the array layout information; determine a sidelobe suppression window function, and determine initial suppression information based on the sidelobe suppression window function.

[0130] Optionally, the determining module 702 is further configured to determine initial array coordinate information based on the array arrangement information, and determine coordinate adjustment parameters based on the array operation information; adjust the initial array coordinate information using the coordinate adjustment parameters to obtain target array coordinate information; and construct an initial array model based on the target array coordinate information.

[0131] Optionally, the determining module 702 is further configured such that the sidelobe suppression window function is...

[0132]

[0133] in, Let θ be the target value for sidelobe suppression at the off-axis angle θ, where θ is the off-axis angle, θmax is the maximum off-axis angle of the sidelobe suppression window, B is the lowest sidelobe level at the center of the saddle shape, A is the level fluctuation value of the sidelobe suppression window, and n is the curve control factor.

[0134] The coordinate adjustment parameter is greater than

[0135]

[0136] Where c is the speed of light, F is the antenna operating frequency, and θscan is the maximum off-axis angle of the beam scan.

[0137] Optionally, the calculation module 704 is further configured to determine the beam pointing information corresponding to the initial array model, calculate the beam steering vector information based on the beam pointing information and the target array coordinate information, and calculate the initial array excitation coefficients corresponding to the initial array model based on the beam steering vector information and the sidelobe suppression window function in the initial suppression information.

[0138] Optionally, the calculation module 704 is further configured to determine equality constraint information based on the beam steering vector information, and determine inequality constraint information based on the sidelobe suppression window function; construct a second-order cone programming problem based on the equality constraint information and the inequality constraint information; and calculate the initial array excitation coefficients corresponding to the initial array model based on the second-order cone programming problem.

[0139] Optionally, the calculation module 704 is further configured to load the initial array excitation coefficients through the initial array model to obtain the radiation pattern corresponding to the initial array model; determine the radiation pattern information corresponding to the radiation pattern, and calculate the quantization index information of the initial array model based on the radiation pattern information and the initial suppression information; compare the quantization index information with preset index information to obtain the radiation performance information of the initial array model.

[0140] Optionally, the optimization module 706 is further configured to, if it is determined from the radiation performance information that the initial array model does not meet the sidelobe Earth matching condition, adjust the initial array information and the initial suppression information to obtain intermediate array information and intermediate suppression information, use the intermediate array information as the initial array information, use the intermediate suppression information as the initial suppression information, and continue to construct the initial array model based on the initial array information; if it is determined from the radiation performance information that the initial array model meets the sidelobe Earth matching condition, use the initial array model corresponding to the initial array information as the target array model, and use the initial array excitation coefficient of the initial array model as the target array excitation coefficient.

[0141] Optionally, the device further includes a control module configured to design the target antenna array according to the target array model; and to perform beam control on the target antenna array according to the target array excitation coefficient.

[0142] The above is a schematic scheme of a satellite-borne phased array antenna beam control device according to this embodiment. It should be noted that the technical solution of this satellite-borne phased array antenna beam control device and the technical solution of the satellite-borne phased array antenna beam control method described above belong to the same concept. For details not described in detail in the technical solution of the satellite-borne phased array antenna beam control device, please refer to the description of the technical solution of the satellite-borne phased array antenna beam control method described above.

[0143] See Figure 8 , Figure 8 This specification shows a schematic diagram of a satellite-borne phased array antenna beam control system according to an embodiment of the present specification. The system includes a beam control component 802 and an antenna array 804, wherein the antenna array 804 is designed by a target array model determined by the above-described satellite-borne phased array antenna beam control method.

[0144] The beam control component 802, in response to an adjustment command for the target beam angle, determines the target array excitation coefficient corresponding to the target beam angle in the array excitation coefficient library, wherein the array excitation coefficient in the array excitation coefficient library is calculated by the above-described spaceborne phased array antenna beam control method.

[0145] The antenna array 804 is used to transmit the communication beam corresponding to the excitation coefficient of the target array to the target beam angle.

[0146] The beam control component can be understood as an intelligent beam control computer system on the satellite, containing a high-performance processor, storage units, and control interfaces. It is responsible for storing the excitation coefficient library, parsing beam pointing instructions, and generating corresponding control signals. The antenna array can be understood as a physical antenna system actually manufactured based on the target array model. It includes array elements, phase shifters, attenuators, and other hardware, and is capable of generating a radiation beam of a specific shape according to the control signals.

[0147] In practical applications, the beam control component can store an array excitation coefficient library. This library pre-calculates and stores a set of excitation coefficients organized in a lookup table format, with each beam pointing angle corresponding to a set of optimized complex excitation coefficients. The beam control component can respond to adjustment commands for the target beam angle by determining the corresponding target array excitation coefficients from the library. The target beam angle is the beam pointing direction required for the satellite to establish a communication link with a specific ground station or user, typically expressed as azimuth and elevation angles.

[0148] In a specific embodiment of this specification, the satellite control system issues an adjustment command: requiring the beam to point at an azimuth angle of 40° and an elevation angle of 50°. The beam control component 802 analyzes the command and determines the target beam angle to be a 50° off-axis angle. The beam control component 802 quickly searches the array excitation coefficient library and locates the target array excitation coefficient corresponding to the 50° pointing direction. The 604-dimensional complex excitation coefficient is decomposed into amplitude and phase control commands. The amplitude command is sent to the digital attenuator of each channel, and the phase command is sent to the digital phase shifter of each channel. Each element of the antenna array 804 radiates electromagnetic waves with specific amplitude and phase according to the command, forming a main lobe beam precisely pointing to 50° through spatial interference. At the same time, a saddle-shaped sidelobe distribution is automatically generated: sidelobes in the nadir region (near 0°) are ≤-35dB, and sidelobes at the edge of the coverage area (near 50°) are ≈-23dB, achieving sidelobe Earth matching and effectively suppressing interference to the nadir region.

[0149] The satellite-borne phased array antenna beam control system provided in this manual achieves the ideal effect of optimal design and immediate usability of the satellite-borne phased array antenna by solidifying the target array model and excitation coefficient library obtained from the previous optimization design into a hardware system and software database. When the satellite is in orbit, only a simple table lookup operation is required to instantly form a high-quality beam with both precise pointing and intelligent anti-interference characteristics. This avoids complex real-time calculations and ensures the reliability and stability of communication quality, providing a high-performance and high-reliability antenna solution for low-Earth orbit satellite communication systems.

[0150] Figure 9 A structural block diagram of a computing device 900 according to one embodiment of this specification is shown. The components of the computing device 900 include, but are not limited to, a memory 910 and a processor 920. The processor 920 is connected to the memory 910 via a bus 930, and a database 950 is used to store data.

[0151] The computing device 900 also includes an access device 940, which enables the computing device 900 to communicate via one or more networks 960. Examples of these networks include Public Switched Telephone Network (PSTN), Local Area Network (LAN), Wide Area Network (WAN), Personal Area Network (PAN), or combinations of communication networks such as the Internet. The access device 940 may include one or more of any type of wired or wireless network interface (e.g., a network interface card (NIC)), such as an IEEE 802.11 Wireless Local Area Network (WLAN) wireless interface, a Wi-MAX (Worldwide Interoperability for Microwave Access) interface, an Ethernet interface, a Universal Serial Bus (USB) interface, a cellular network interface, a Bluetooth interface, or a Near Field Communication (NFC) interface.

[0152] In one embodiment of this specification, the above-described components of the computing device 900 and Figure 9 Other components, not shown, can also be connected to each other, for example, via a bus. It should be understood that... Figure 9 The block diagram of the computing device shown is for illustrative purposes only and is not intended to limit the scope of this specification. Those skilled in the art can add or replace other components as needed.

[0153] The computing device 900 can be any type of stationary or mobile computing device, including mobile computers or mobile computing devices (e.g., tablet computers, personal digital assistants, laptop computers, notebook computers, netbooks, etc.), mobile phones (e.g., smartphones), wearable computing devices (e.g., smartwatches, smart glasses, etc.) or other types of mobile devices, or stationary computing devices such as desktop computers or personal computers (PCs). The computing device 900 can also be a mobile or stationary server.

[0154] The processor 920 is used to execute the following computer-executable instructions, which, when executed by the processor, implement the steps of the above-described satellite phased array antenna beam control method.

[0155] The above is a schematic representation of a computing device according to this embodiment. It should be noted that the technical solution of this computing device and the technical solution of the aforementioned spaceborne phased array antenna beam control method belong to the same concept. Details not described in detail in the technical solution of the computing device can be found in the description of the technical solution of the aforementioned spaceborne phased array antenna beam control method.

[0156] An embodiment of this specification also provides a computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the above-described satellite phased array antenna beam control method.

[0157] The above is an illustrative scheme of a computer-readable storage medium according to this embodiment. It should be noted that the technical solution of this storage medium belongs to the same concept as the technical solution of the above-described satellite-borne phased array antenna beam control method. For details not described in detail in the technical solution of the storage medium, please refer to the description of the technical solution of the above-described satellite-borne phased array antenna beam control method.

[0158] An embodiment of this specification also provides a computer program product, including a computer program or instructions that, when executed by a processor, implement the steps of the above-described spaceborne phased array antenna beam control method.

[0159] The above is an illustrative scheme of a computer program product according to this embodiment. It should be noted that the technical solution of this computer program product and the technical solution of the above-described satellite-borne phased array antenna beam control method belong to the same concept. For details not described in detail in the technical solution of the computer program product, please refer to the description of the technical solution of the above-described satellite-borne phased array antenna beam control method.

[0160] The foregoing has described specific embodiments of this specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in a different order than that shown in the embodiments and may still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require the specific or sequential order shown to achieve the desired result. In some embodiments, multitasking and parallel processing are possible or may be advantageous.

[0161] The computer instructions include computer program code, which may be in the form of source code, object code, executable file, or certain intermediate forms. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording media, USB flash drive, portable hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signals, telecommunication signals, and software distribution media, etc. It should be noted that the content included in the computer-readable medium may be appropriately added or removed according to the requirements of patent practice. For example, in some regions, according to patent practice, computer-readable media may not include electrical carrier signals and telecommunication signals.

[0162] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that the embodiments in this specification are not limited to the described order of actions, because according to the embodiments in this specification, some steps can be performed in other orders or simultaneously. Furthermore, those skilled in the art should also understand that the embodiments described in this specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to the embodiments in this specification.

[0163] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0164] The preferred embodiments disclosed above are merely illustrative of this specification. Optional embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the embodiments described in this specification. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the embodiments, thereby enabling those skilled in the art to better understand and utilize this specification.

Claims

1. A beam control method for a spaceborne phased array antenna, characterized in that, include: Initial array information and initial suppression information are determined, and an initial array model is constructed based on the initial array information. The initial suppression information includes a sidelobe suppression window function that satisfies the sidelobe Earth matching condition. The sidelobe suppression window function is... in, Let θ be the target value for sidelobe suppression at the off-axis angle θ, where θ is the off-axis angle, θmax is the maximum off-axis angle of the sidelobe suppression window, B is the lowest sidelobe level at the center of the saddle shape, A is the level fluctuation value of the sidelobe suppression window, and n is the curve control factor. The initial array excitation coefficients corresponding to the initial array model are calculated using the initial suppression information, and the radiation performance information of the initial array model is determined using the initial array excitation coefficients. Based on the radiation performance information, the initial array information and the initial suppression information are iteratively optimized until the target array model and the target array excitation coefficients of the target array model that satisfy the sidelobe earth matching condition are obtained. The target array model is used to design the target antenna array, and the target array excitation coefficients are used to control the communication beam of the target antenna array.

2. The method according to claim 1, characterized in that, Determine the initial array information and initial suppression information, including: Determine the array unit size information, array operation information, and array layout information, and determine the initial array information based on the array unit size information, array operation information, and array layout information; Determine the sidelobe suppression window function, and determine the initial suppression information based on the sidelobe suppression window function; Constructing an initial array model based on the initial array information includes: The initial array coordinate information is determined based on the array layout information, and the coordinate adjustment parameters are determined based on the array operation information. The initial array coordinate information is adjusted using the coordinate adjustment parameters to obtain the target array coordinate information; An initial array model is constructed based on the target array coordinate information.

3. The method according to claim 2, characterized in that, The coordinate adjustment parameter is greater than Where c is the speed of light, F is the antenna operating frequency, and θscan is the maximum off-axis angle of the beam scan.

4. The method according to claim 2, characterized in that, The calculation of the initial array excitation coefficients corresponding to the initial array model using the initial suppression information includes: Determine the beam pointing information corresponding to the initial array model, and calculate the beam steering vector information based on the beam pointing information and the target array coordinate information; Based on the beam steering vector information and the sidelobe suppression window function in the initial suppression information, the initial array excitation coefficients corresponding to the initial array model are calculated.

5. The method according to claim 4, characterized in that, Based on the beam steering vector information and the sidelobe suppression window function in the initial suppression information, the initial array excitation coefficients corresponding to the initial array model are calculated, including: Equality constraint information is determined based on the beam steering vector information, and inequality constraint information is determined based on the sidelobe suppression window function; a second-order cone programming problem is constructed based on the equality constraint information and the inequality constraint information. Calculate the initial array excitation coefficients corresponding to the initial array model based on the second-order cone programming problem.

6. The method according to claim 1, characterized in that, The radiation performance information of the initial array model is determined by the initial array excitation coefficients, including: By loading the initial array excitation coefficients onto the initial array model, the radiation pattern corresponding to the initial array model is obtained; Determine the radiation pattern information corresponding to the radiation pattern, and calculate the quantization index information of the initial array model based on the radiation pattern information and the initial suppression information; The quantified index information is compared with the preset index information to obtain the radiation performance information of the initial array model.

7. The method according to claim 1, characterized in that, Iterative optimization of the initial array information and the initial suppression information based on the radiation performance information includes: If the initial array model does not meet the sidelobe Earth matching condition based on the radiation performance information, the initial array information and the initial suppression information are adjusted to obtain intermediate array information and intermediate suppression information. The intermediate array information is used as the initial array information, and the intermediate suppression information is used as the initial suppression information. The initial array model is then constructed based on the initial array information. If the initial array model satisfies the sidelobe Earth matching condition based on the radiation performance information, the initial array model corresponding to the initial array information is used as the target array model, and the initial array excitation coefficient of the initial array model is used as the target array excitation coefficient.

8. The method according to claim 1, characterized in that, The method further includes: Design the target antenna array based on the target array model; Beam control is performed using the target antenna array according to the target array excitation coefficient.

9. A beam control system for a spaceborne phased array antenna, characterized in that, The system includes a beam control component and an antenna array, wherein the antenna array is obtained by designing a target array model determined by the method described in any one of claims 1-8; The beam control component, in response to an adjustment command for a target beam angle, determines a target array excitation coefficient corresponding to the target beam angle in an array excitation coefficient library, wherein the array excitation coefficients in the array excitation coefficient library are calculated by the method described in any one of claims 1-8; The antenna array is used to transmit the communication beam corresponding to the excitation coefficient of the target array to the target beam angle.

10. A computing device, characterized in that, include: Memory and processor; The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions, which, when executed by the processor, implement the steps of the method according to any one of claims 1 to 8.

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