A dynamic beam adjustment system for low and medium earth orbit satellite communications

Abstract

The application relates to the technical field of satellite communication, in particular to a dynamic beam adjustment system for medium and low orbit satellite communication. The system comprises a beam demand perception unit, a dynamic beam calculation unit, a beam execution adjustment unit and a satellite-ground coordination unit. The dynamic beam calculation unit offsets the influence of complex environment on beam coverage through a multi-factor collaborative compensation mechanism. The beam execution adjustment unit realizes accurate beam pointing and interference suppression through an adaptive phase optimization algorithm. The application calculates the theoretical pointing angle of the beam based on spherical geometry, determines the compensation amount in combination with satellite movement, user movement and atmospheric refraction, dynamically adjusts the weight of each compensation amount and combines the compensation amounts into a total compensation amount according to the satellite elevation angle, user terminal movement speed and communication link signal-to-noise ratio, and finally obtains the actual beam pointing angle, so that the coupling influence of multi-factors on beam coverage in complex environment is effectively offset, and the beam pointing precision is improved.

Description

Technical Field

[0001] This invention relates to the field of satellite communication technology, and more specifically, to a dynamic beam adjustment system for medium and low Earth orbit satellite communication. Background Technology

[0002] Low and medium Earth orbit (LEO) satellite communication systems, due to their advantages of low orbital altitude, short signal propagation delay, and ample link bandwidth, have become one of the key technologies for building a seamless global communication network. In practical applications, there is continuous relative motion between LEO satellites and ground user terminals, and signal transmission is susceptible to atmospheric refraction interference, leading to beam coverage shift and decreased communication link stability. At the same time, the spatial distribution of users within the satellite coverage area is dynamically uneven, and traditional fixed beam pointing and power configuration methods are difficult to adapt to this change, easily resulting in problems such as large beam pointing deviation and unreasonable resource allocation. Therefore, dynamic beam adjustment technology is a core requirement for ensuring the quality of LEO satellite communication.

[0003] In the existing technology, relevant patents have already conducted research in the field of low-Earth orbit (LEO) satellite beam scheduling and optimization. For example, Chinese patent CN202411453132.X discloses a method and system for LEO satellite beam scheduling optimization based on simulated annealing algorithm. First, a model of the satellite communication system and communication service distribution is established. Then, a channel model between the satellite and the terminal is established. Subsequently, constraints are determined and the optimal beam scheduling problem is mathematically modeled. With the goal of improving coverage and reducing inter-beam interference, the simulated annealing algorithm is used to solve the problem, achieving beam pattern optimization and overall system performance improvement. Furthermore, Chinese patent CN202411830481.9 discloses a method, device, equipment, and storage medium for LEO satellite beam scheduling and resource allocation. This method determines user time slot priorities, divides user groups and constructs a beam position interference matrix. Based on the priorities and interference matrix, time slots are allocated to generate hopping beam patterns. Within the update cycle, target users for each time slot are determined, and resources are allocated according to service priorities. The above methods achieve interference isolation and time slot allocation based on user priority and grouping, and multi-user resource scheduling in a single time slot to improve spectrum utilization and system throughput.

[0004] Despite the design advantages of the aforementioned technical solutions, they also suffer from the following technical shortcomings: Firstly, they fail to optimize beam pointing accuracy for multi-factor coupled scenarios. Chinese patent CN202411453132.X optimizes the beam pattern through algorithms, while Chinese patent CN202411830481.9 focuses on user priority-based scheduling. Neither CN202411453132.X nor CN202411830481.9 considers the coupling effects of satellite motion, user movement, and atmospheric refraction, nor does it address the underlying causes. The current dynamic beam adjustment compensation strategy based on real-time scene parameters is insufficient to solve beam pointing deviation problems in complex environments. Secondly, it fails to combine dynamic data with a closed-loop mechanism to optimize resource allocation and interference suppression: Chinese patents CN202411453132.X and CN202411830481.9 do not utilize dynamic data such as user distribution density and satellite payload status from satellite-ground collaborative transmission, making it impossible to achieve differentiated configuration of multi-beam power. Furthermore, they lack a feedback correction mechanism for actual beam coverage parameters, making it difficult to effectively suppress mutual coupling interference between adjacent beams and improve resource utilization efficiency. Therefore, we propose a dynamic beam adjustment system for low- and medium-Earth orbit satellite communication. Summary of the Invention

[0005] The purpose of this invention is to provide a dynamic beam adjustment system for medium and low Earth orbit satellite communication, so as to solve the problems mentioned in the background art, such as the failure to optimize beam pointing accuracy for multi-factor coupling scenarios and the failure to combine dynamic data and closed-loop mechanisms to optimize resource allocation and interference suppression.

[0006] To address the aforementioned technical problems, the present invention aims to provide a dynamic beam adjustment system for low- and medium-Earth orbit satellite communication, comprising:

[0007] A beam demand sensing unit is used to collect basic physical parameters, including user terminal side parameters and satellite side parameters, within the coverage area of ​​medium and low orbit satellites.

[0008] The dynamic beam calculation unit calculates core beam parameters, including beam pointing angle and transmit power adaptation value, based on the basic physical parameters of the beam demand sensing unit and the relative motion relationship between the satellite and the user. It also uses a multi-factor collaborative compensation mechanism to offset the impact of complex environments on beam coverage. The multi-factor collaborative compensation mechanism achieves dynamic correction of the pointing angle through weighted coupling of satellite motion compensation, user movement compensation, and atmospheric refraction correction. The compensation weights of satellite motion compensation, user movement compensation, and atmospheric refraction correction are adjusted in real time according to the communication scenario.

[0009] The beam execution adjustment unit is used to convert the core beam parameters output by the dynamic beam calculation unit into physical control commands, achieve precise beam pointing and interference suppression through an adaptive phase optimization algorithm, and complete multi-beam power configuration based on the transmit power adaptation value output by the dynamic beam calculation unit to achieve real-time resource scheduling.

[0010] The satellite-ground coordination unit is used to establish a two-way data link between the satellite and the ground station, transmit the spatial density of user distribution and satellite payload operating status parameters, and support the updating of basic data for beam adjustment.

[0011] The performance monitoring unit is used to detect the actual coverage parameters of the beam and feed the monitoring data back to the dynamic beam calculation unit and the beam execution adjustment unit.

[0012] As a further improvement to this technical solution, the beam demand sensing unit includes a user parameter sensing module and a satellite parameter sensing module, wherein:

[0013] The user parameter sensing module is used to receive uplink signaling and detection signals transmitted by the user terminal, and to collect user terminal-side parameters including real-time spatial coordinates, movement speed, service signal bandwidth, and communication link signal-to-noise ratio.

[0014] The satellite parameter sensing module, based on the onboard navigation receiver and payload status sensor, collects satellite-side parameters including satellite orbital position, velocity vector, and elevation angle.

[0015] As a further improvement to this technical solution, the beam demand sensing unit also includes a data preprocessing module. This data preprocessing module processes the basic physical parameters collected by the user parameter sensing module and the satellite parameter sensing module, specifically including:

[0016] The real-time spatial coordinates of the user terminal collected by the user parameter sensing module and the satellite orbit position collected by the satellite parameter sensing module are converted into three-dimensional coordinates in the WGS84 geodetic coordinate system.

[0017] Anomaly identification is performed on the collected user terminal side parameters and satellite side parameters. When the user terminal's movement speed exceeds the normal movement range of the ground terminal or the satellite's elevation angle is lower than the effective communication elevation angle threshold of medium and low orbit satellites, it is marked as abnormal data and a re-acquisition process is triggered.

[0018] Add a synchronization timestamp to the verified user terminal-side parameters and satellite-side parameters.

[0019] As a further improvement to this technical solution, the dynamic beam calculation unit includes a basic parameter calculation module. This module calculates the theoretical values ​​of the core beam parameters based on the basic physical parameters of the beam demand sensing unit, specifically including:

[0020] Based on the real-time spatial coordinates of the user terminal and the satellite orbit position, the theoretical beam pointing angle is calculated using spherical geometric relationships. This theoretical beam pointing angle includes the theoretical azimuth angle. Compared with theoretical pitch angle ;

[0021] Based on the straight-line distance between the user terminal and the satellite Signal-to-noise ratio of communication link and service signal bandwidth Calculate the initial transmit power value , This serves as a reference value for the transmit power adaptation.

[0022] As a further improvement to this technical solution, the dynamic beam calculation unit also includes a multi-factor compensation module, which is used to calculate the compensation components of the pointing angle, specifically including:

[0023] Satellite tangential velocity collected by beam demand sensing unit Straight-line distance between user terminal and satellite Calculate signal propagation delay and combined , and Determine the satellite motion compensation amount ;

[0024] User terminal movement speed collected by beam demand sensing unit distance from the line Combined with signal propagation delay Determine the amount of user mobility compensation ;

[0025] Satellite elevation angles collected by beam demand sensing units Introducing atmospheric refraction correction factor Determine the atmospheric refraction correction amount .

[0026] As a further improvement to this technical solution, the dynamic beam calculation unit also includes a weight synthesis module. The weight synthesis module dynamically adjusts the compensation weights based on the communication scenario and synthesizes the final parameters, including the following steps:

[0027] S230.1 Obtain the satellite elevation angle collected by the beam demand sensing unit. User terminal movement speed and the signal-to-noise ratio of the communication link And based on satellite elevation angle User terminal movement speed and the signal-to-noise ratio of the communication link Determine the current communication scenario;

[0028] S230.2 For the determined communication scenario, configure corresponding weighting coefficients for satellite motion compensation, user motion compensation, and atmospheric refraction correction. ,and ;

[0029] S230.3 Receive satellite motion compensation amount output by the multi-factor compensation module User mobility compensation amount Atmospheric refraction correction and according to weighting coefficients Combined into total compensation amount ;

[0030] S230.4, Call the theoretical azimuth angle output by the basic parameter calculation module. Compared with theoretical pitch angle Combined with the total compensation amount Make corrections to obtain the actual beam pointing angle. ;

[0031] S230.5, Call the initial transmit power value output by the basic parameter calculation module. Based on total compensation amount Adjustments are made to generate transmit power adaptation values. .

[0032] As a further improvement to this technical solution, the beam adjustment unit includes a command parsing module, which converts the core beam parameters into physical control commands, including the following steps:

[0033] S310.1 Receive the actual beam pointing angle output by the dynamic beam calculation unit. Adaptation value with transmit power The validity of the parameters is verified to ensure that... Within the adjustable range of the pointing angle of the phased array antenna, Within the rated power range of the power amplifier;

[0034] S310.2. Based on the element spacing and operating wavelength parameters of the phased array antenna, the actual beam pointing angle is determined. The phase difference requirement of each array element is converted into a digital phase control word containing the phase adjustment amount, and the digital phase control word corresponds one-to-one with the array element number.

[0035] S310.3. Based on the gain curve parameters of the power amplifier, adjust the transmit power to match the parameters. This is converted into a power adjustment command, which includes a quantized value of the power amplification factor, and the quantized value is matched with the transmit power. They exhibit a linear mapping relationship.

[0036] As a further improvement to this technical solution, the beam execution adjustment unit also includes a beam control module. The beam control module realizes beam control and resource scheduling based on the physical control commands output by the command parsing module, including the following steps:

[0037] S320.1 The digital phase control word output by the receiving command parsing module applies a corresponding phase adjustment to each element of the phased array antenna through an adaptive phase optimization algorithm, so that the main lobe of the beam points to the actual beam pointing angle. ;

[0038] S320.2 During beam pointing, the mutual interference signal of adjacent beams is collected through the antenna receiver. When the mutual interference signal strength exceeds the preset threshold, the phase compensation amount of the edge array elements is dynamically adjusted until the mutual interference signal strength drops below the threshold.

[0039] S320.3 The power adjustment command output by the receiving command parsing module, combined with the user distribution spatial density transmitted by the satellite-ground coordination unit, adjusts the transmit power to match the specified value. The power is allocated to each sub-beam within the coverage area according to density ratio, prioritizing the power needs of high-density user areas, thus completing the multi-beam power configuration.

[0040] As a further improvement to this technical solution, the satellite-ground coordination unit includes a bidirectional link management module and a data synchronization module, wherein:

[0041] The bidirectional link management module establishes an anti-interference communication link between the satellite and the ground station through the Ka band, uses frequency hopping spread spectrum technology to resist channel noise, and monitors the link bit error rate in real time. When the link bit error rate exceeds a preset threshold, a link reconnection mechanism is triggered.

[0042] The data synchronization module transmits user distribution spatial density data to the beam demand sensing unit at a preset cycle, including the number of user terminals and service types in different latitude and longitude grids; it also receives satellite payload calibration parameters sent by the ground station and updates operating status parameters (such as satellite antenna gain, power amplifier efficiency, etc.) to provide a real-time payload performance benchmark for the dynamic beam calculation unit.

[0043] As a further improvement to this technical solution, the performance monitoring unit includes a coverage parameter acquisition module and a feedback control module, wherein:

[0044] The coverage parameter acquisition module acquires the signal strength distribution, 3dB beamwidth, and edge roll-off rate of the actual beam coverage area through the beacon receiver in the satellite payload, and simultaneously records the actual measured value of the beam pointing angle. Compared with theoretical value deviation ;

[0045] The feedback control module feeds back the signal strength distribution and beamwidth data to the dynamic beam calculation unit to optimize the transmit power adaptation value. The calculation model; and the pointing angle deviation The feedback is sent to the beam control unit as a correction value for the phase control word to achieve closed-loop control.

[0046] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0047] 1. This invention constructs a multi-factor collaborative compensation mechanism through a dynamic beam calculation unit. First, it calculates the theoretical beam pointing angle based on spherical geometry. Then, it determines the compensation amount by combining satellite motion, user movement, and atmospheric refraction. At the same time, it determines the communication scenario based on the satellite elevation angle, user terminal movement speed, and communication link signal-to-noise ratio. It dynamically adjusts the weights of each compensation amount and synthesizes them into a total compensation amount, finally obtaining the actual beam pointing angle. This effectively offsets the coupling effect of multiple factors on beam coverage in complex environments and improves beam pointing accuracy.

[0048] 2. This invention establishes an anti-interference two-way link through a satellite-ground cooperative unit using Ka-band and frequency hopping spread spectrum technology, transmitting user distribution spatial density and satellite payload calibration parameters in real time. Then, the beam adjustment unit distributes the transmit power adaptation value to each sub-beam according to the user density ratio, prioritizing the needs of high-density user areas, realizing dynamic adaptation and scheduling of multi-beam power, avoiding insufficient signal in high-density areas or power waste in low-density areas, and improving the utilization efficiency of satellite communication resources.

[0049] 3. This invention collects actual beam coverage parameters through a performance monitoring unit, feeds back signal strength and beamwidth data to a dynamic beam calculation unit to optimize the transmit power calculation model, feeds back pointing angle deviation to a beam adjustment unit to correct the phase control word of the phased array elements, and combines edge element phase compensation adjustment to construct a closed-loop beam adjustment control, effectively suppressing mutual coupling interference between adjacent beams and ensuring the stability of the communication link. Attached Figure Description

[0050] Figure 1 This is a schematic diagram of the dynamic beam adjustment system framework in this invention;

[0051] The meanings of the labels in the diagram are as follows:

[0052] 100. Beam demand sensing unit; 110. User parameter sensing module; 120. Satellite parameter sensing module; 130. Data preprocessing module;

[0053] 200. Dynamic beamforming calculation unit; 210. Basic parameter calculation module; 220. Multi-factor compensation module; 230. Weight synthesis module;

[0054] 300. Beam adjustment unit; 310. Command parsing module; 320. Beam control module;

[0055] 400. Satellite-Ground Collaboration Unit; 410. Two-Way Link Management Module; 420. Data Synchronization Module;

[0056] 500. Performance monitoring unit; 510. Coverage parameter acquisition module; 520. Feedback control module. Detailed Implementation

[0057] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0058] like Figure 1 As shown, this embodiment provides a dynamic beam adjustment system for low- and medium-Earth orbit satellite communication, including:

[0059] Beam demand sensing unit 100 is used to collect basic physical parameters, including user terminal side parameters and satellite side parameters, within the coverage area of ​​medium and low orbit satellites.

[0060] In this embodiment, the beam demand sensing unit 100 includes a user parameter sensing module 110 and a satellite parameter sensing module 120, wherein:

[0061] The user parameter sensing module 110 is used to receive uplink signaling and detection signals transmitted by the user terminal, and to collect user terminal-side parameters including real-time spatial coordinates, movement speed, service signal bandwidth, and communication link signal-to-noise ratio.

[0062] Specifically, the user parameter sensing module 110 receives uplink signaling and probe signals transmitted by the user terminal through a receiving link that communicates with the user terminal, and collects user terminal-side parameters from the above signals; wherein, the operating frequency band of the receiving link matches the uplink communication frequency band of the user terminal to ensure stable reception of uplink signaling and probe signals.

[0063] Meanwhile, during parameter acquisition, real-time spatial coordinates are extracted from the location information reported by the user terminal via uplink signaling. The speed of movement is obtained by calculating the ratio of the distance difference between adjacent coordinates to the acquisition time difference from the real-time spatial coordinates carried in multiple sets of continuously received uplink signaling or probe signals. The service signal bandwidth is directly extracted from the service configuration information carried in the uplink signaling of the user terminal. The signal-to-noise ratio of the communication link is determined by analyzing the ratio of the signal power to the noise power of the received probe signal. All acquired parameters are stored in real time in the temporary data buffer area inside the user parameter sensing module 110.

[0064] The satellite parameter sensing module 120, based on the onboard navigation receiver and payload status sensor, collects satellite-side parameters including satellite orbital position, motion velocity vector, and elevation angle.

[0065] Specifically, the satellite parameter sensing module 120 relies on the onboard navigation receiver and payload status sensor to complete the acquisition of satellite-side parameters. The onboard navigation receiver is used to acquire the satellite's orbital position data and calculates the satellite's current orbital position information by receiving navigation satellite signals. The payload status sensor is used to acquire the satellite's motion velocity vector and elevation angle. The motion velocity vector is obtained by the sensor detecting the magnitude and direction of the satellite's speed during its orbital operation, while the elevation angle is calculated by the sensor monitoring the satellite's altitude relative to the Earth's surface and combining it with the satellite's orbital characteristics. The acquired parameters such as satellite orbital position, motion velocity vector, and elevation angle are summarized according to a preset period (matching the acquisition period of the user parameter sensing module 110) to ensure that the acquisition rhythm of satellite-side parameters and user terminal-side parameters is coordinated.

[0066] In this embodiment, the beam demand sensing unit 100 further includes a data preprocessing module 130. The data preprocessing module 130 is used to process the basic physical parameters collected by the user parameter sensing module 110 and the satellite parameter sensing module 120, specifically including:

[0067] The real-time spatial coordinates of the user terminal collected by the user parameter sensing module 110 and the satellite orbit position collected by the satellite parameter sensing module 120 are converted into three-dimensional coordinates in the WGS84 geodetic coordinate system.

[0068] Anomaly identification is performed on the collected user terminal side parameters and satellite side parameters. When the user terminal's movement speed exceeds the normal movement range of the ground terminal or the satellite's elevation angle is lower than the effective communication elevation angle threshold of medium and low orbit satellites, it is marked as abnormal data and a re-acquisition process is triggered.

[0069] Add a synchronization timestamp to the verified user terminal-side parameters and satellite-side parameters.

[0070] Specifically, in the coordinate system transformation stage, for the real-time spatial coordinates of the user terminal collected by the user parameter sensing module 110 and the satellite orbit position collected by the satellite parameter sensing module 120, a unified coordinate transformation rule is adopted to convert both types of coordinates into three-dimensional coordinates under the WGS84 geodetic coordinate system, so as to ensure that the coordinate reference is consistent in the subsequent calculation process.

[0071] Specifically, in the outlier identification stage, anomaly judgment criteria are preset: the user terminal's movement speed exceeds the normal movement range of ground terminals (such as the movement speed range of common ground terminals such as pedestrians and vehicles), and the satellite elevation angle is lower than the effective communication elevation angle threshold of medium and low orbit satellites (this threshold is set according to the minimum altitude requirement of medium and low orbit satellite communication). When the collected parameters meet any of the above anomaly criteria, they are immediately marked as abnormal data, and a re-collection instruction is sent to the corresponding acquisition module (user parameter sensing module 110 or satellite parameter sensing module 120). After the re-collection instruction is triggered, the acquisition module acquires the parameters again according to the original acquisition process. If the data is still abnormal after multiple consecutive acquisitions (usually 3 times), the data is marked as invalid data and skipped to prevent abnormal data from entering subsequent calculations.

[0072] Specifically, in the process of adding synchronization timestamps, timestamps are added to the user terminal-side parameters and satellite-side parameters after coordinate transformation and outlier verification, based on the satellite's own time reference (which is consistent with the overall satellite system time). The timestamp format is "year-month-day hour:minute:second:millisecond" to ensure that each set of parameters corresponds to a clear acquisition time, providing time synchronization guarantee for subsequent data interaction with the dynamic beam computing unit 200.

[0073] The dynamic beam calculation unit 200 calculates core beam parameters, including beam pointing angle and transmit power adaptation value, based on the basic physical parameters of the beam demand sensing unit 100 and the relative motion relationship between the satellite and the user. It also uses a multi-factor collaborative compensation mechanism to offset the impact of complex environment on beam coverage. The multi-factor collaborative compensation mechanism achieves dynamic correction of pointing angle through weighted coupling of satellite motion compensation, user movement compensation, and atmospheric refraction correction. The compensation weights of satellite motion compensation, user movement compensation, and atmospheric refraction correction are adjusted in real time according to the communication scenario.

[0074] In this embodiment, the dynamic beam calculation unit 200 includes a basic parameter calculation module 210. The basic parameter calculation module 210 calculates the theoretical values ​​of the core beam parameters based on the basic physical parameters of the beam demand sensing unit 100, specifically including:

[0075] Based on the real-time spatial coordinates of the user terminal and the satellite orbit position, the theoretical beam pointing angle is calculated using spherical geometric relationships. The theoretical beam pointing angle includes the theoretical azimuth angle. Compared with theoretical pitch angle ;

[0076] Based on the straight-line distance between the user terminal and the satellite Signal-to-noise ratio of communication link and service signal bandwidth Calculate the initial transmit power value , This serves as a reference value for the transmit power adaptation.

[0077] Specifically, the basic parameter calculation module 210 relies on the algorithm unit of the spaceborne embedded computing platform to perform calculations based on the basic physical parameters output by the beam demand sensing unit 100. First, it calls the real-time spatial coordinates of the user terminal and the satellite orbit position, and converts the two types of coordinates into the Earth's central rectangular coordinate system coordinates based on the ellipsoidal parameters (major axis, flattening, and other recognized geographical parameters) of the WGS84 geodetic coordinate system. Then, it calculates the theoretical beam pointing angle, i.e., the theoretical azimuth angle, through spherical geometric relationships. Compared with theoretical pitch angle Among them, the theoretical azimuth angle The theoretical elevation angle is the horizontal angle formed by rotating the user terminal clockwise from true north to the direction of the satellite. The first step is to rotate the user terminal's horizon upwards to the vertical angle pointing towards the satellite (the effect of the Earth's curvature on the horizon is deducted during the calculation). The second step is to calculate the straight-line distance between the user terminal and the satellite using the spatial distance formula, based on the transformed rectangular coordinates. Simultaneously, the signal-to-noise ratio of the communication link collected by the beam demand sensing unit 100 is invoked. and service signal bandwidth To meet the minimum requirements for stable transmission of service signals With demand as the objective, and considering signal free space loss (the degree of loss and...) Proportional to, and The initial transmit power value is calculated by taking into account the positive correlation and the reserved margin (to cope with short-term signal fluctuations). ,make sure As a benchmark for transmission power adaptation, it meets the basic requirements of low- and medium-Earth orbit satellite communication.

[0078] In this embodiment, the dynamic beam calculation unit 200 further includes a multi-factor compensation module 220, which is used to calculate each compensation component of the pointing angle, specifically including:

[0079] Satellite tangential velocity collected by beam demand sensing unit 100 Straight-line distance between user terminal and satellite Calculate signal propagation delay and combined , and Determine the satellite motion compensation amount ;

[0080] User terminal movement speed collected by beam demand sensing unit 100 distance from the line Combined with signal propagation delay Determine the amount of user mobility compensation ;

[0081] Satellite elevation angle collected by beam demand sensing unit 100 Introducing atmospheric refraction correction factor Determine the atmospheric refraction correction amount .

[0082] Specifically, the multi-factor compensation module 220 calculates each compensation component of the pointing angle step by step based on the parameters collected by the beam demand sensing unit 100 and the output parameters of the basic parameter calculation module 210:

[0083] First, the straight-line distance is calculated based on the basic parameter calculation module 210. Combined with the speed of signal propagation in space (speed of light) Using generally accepted physical constants, through the formula Calculate signal propagation delay ;

[0084] Subsequently, the satellite tangential velocity collected by the beam demand sensing unit 100 was invoked. , combined Calculated and straight-line distance Considering the satellite in The interior will undergo tangential displacement (the amount of displacement is...) ), and the displacement is much smaller than Using the principle of small-angle approximation, through the formula Determine the satellite motion compensation amount ;

[0085] Then, the user terminal's motion speed, collected by the beam demand sensing unit 100, is invoked. Similarly, , and Through formula Determine the amount of user mobility compensation. ;

[0086] Finally, the satellite elevation angle collected by the beam demand sensing unit 100 is invoked. An atmospheric refraction correction coefficient adapted to the medium and low orbit satellite communication environment is introduced. ( The value is based on Adjustment, The smaller the value, the thicker the atmosphere the signal has to pass through, and the stronger the refraction effect. The larger the value, the lower the value. The smaller the value, the more easily it can be fine-tuned via the spaceborne platform interface to adapt to the atmospheric characteristics of different regions; simultaneously... Calculated based on the atmospheric refraction model specified in ITU-RP.834 Recommendation published by the International Telecommunication Union (ITU), this model has been widely verified and adopted in atmospheric refraction compensation scenarios in the field of satellite communications. (The formula is used to calculate this model.) Determine the atmospheric refraction correction amount .

[0087] In this embodiment, the dynamic beamforming calculation unit 200 further includes a weight synthesis module 230. The weight synthesis module 230 dynamically adjusts the compensation weights based on the communication scenario and synthesizes the final parameters, including the following steps:

[0088] S230.1, Obtain the satellite elevation angle collected by the beam demand sensing unit 100. User terminal movement speed and the signal-to-noise ratio of the communication link And based on satellite elevation angle User terminal movement speed and the signal-to-noise ratio of the communication link Determine the current communication scenario; for example: To stabilize the scene, For complex scenarios, For general scenarios;

[0089] S230.2 For the determined communication scenario, configure corresponding weighting coefficients for satellite motion compensation, user motion compensation, and atmospheric refraction correction. ,and For example, stable scenario configuration General scenario configuration ;

[0090] S230.3, Receive satellite motion compensation amount output by multi-factor compensation module 220 User mobility compensation amount Atmospheric refraction correction and according to weighting coefficients Combined into total compensation amount It should be noted that the total compensation amount... Physically, it includes the total azimuth compensation component. With pitch angle total compensation component In actual calculations, the azimuth components of the satellite motion compensation, user motion compensation, and atmospheric refraction correction are calculated. By weight Synthesized For their respective pitch angle components By weight Synthesized This fully reflects the compensation logic of the total compensation amount in the beam pointing angle (including azimuth and elevation dimensions).

[0091] S230.4, Call the theoretical azimuth angle output by the basic parameter calculation module 210. Compared with theoretical pitch angle Combined with the total compensation amount Make corrections to obtain the actual beam pointing angle. Call the theoretical azimuth angle Compared with theoretical pitch angle ,Will Overlay Obtain the actual azimuth angle ,Will Overlay Obtain the actual pitch angle This ultimately forms the actual beam pointing angle. ;

[0092] S230.5, Call the initial transmit power value output by the basic parameter calculation module 210. Based on total compensation amount Adjustments are made to generate transmit power adaptation values. The output of the basic parameter calculation module 210 is called. Based on total compensation amount Adjust power:

[0093] like A larger value (meaning a larger beam pointing deviation correction, and potentially a greater difference in signal loss between the actual and theoretical propagation paths) is then calculated according to the formula. Increase power appropriately;

[0094] like If the deviation is small (small correction amount, small loss difference), then Finally, the transmit power adaptation value is generated. ;in The preset maximum compensation angle threshold is used to avoid excessive power increase.

[0095] The beam execution adjustment unit 300 is used to convert the core beam parameters output by the dynamic beam calculation unit 200 into physical control commands, achieve precise beam pointing and interference suppression through an adaptive phase optimization algorithm, and complete multi-beam power configuration based on the transmit power adaptation value output by the dynamic beam calculation unit 200 to achieve real-time resource scheduling.

[0096] Understandably, the beam execution adjustment unit 300 uses the satellite carrier beam control hardware platform as its core carrier. This platform integrates a phased array antenna, a power amplifier, a digital signal processor, and a signal acquisition unit. It can receive the core beam parameters output by the dynamic beam calculation unit 200 in real time, and at the same time establish a data interaction link with the satellite-ground coordination unit 400. This provides hardware support for command parsing, beam control, and resource scheduling, ensuring the accurate generation and execution of physical control commands and matching the dynamic adjustment requirements of medium and low orbit satellite communication.

[0097] Furthermore, the core components and functions of the star carrier beam control hardware platform are as follows:

[0098] Phased array antenna: As the core component for beam transmission and reception, it has the ability to generate multiple beams and adjust the direction. Its array elements are arranged according to preset rules (such as rectangular array or circular array), and the array element spacing and working wavelength parameters are pre-fixed in the hardware configuration.

[0099] Power amplifier: Used to adapt the beam signal to the transmit power value. It amplifies power and has a gain curve parameter storage function, and can output corresponding power according to power adjustment commands;

[0100] Digital signal processor: It undertakes the tasks of instruction parsing, phase calculation and interference signal processing, and supports real-time operation of adaptive phase optimization algorithms;

[0101] Signal acquisition unit: Integrated into the antenna receiver, it is used to acquire mutual interference signals between adjacent beams and transmit the signal strength data to the digital signal processor for analysis.

[0102] In this embodiment, the beam adjustment unit 300 includes an instruction parsing module 310, which converts the core beam parameters into physical control instructions, including the following steps:

[0103] S310.1 Receive the actual beam pointing angle output by the dynamic beam calculation unit 200 Adaptation value with transmit power The validity of the parameters is verified to ensure that... Within the adjustable range of the pointing angle of the phased array antenna, Within the rated power range of the power amplifier;

[0104] Specifically, during verification, the hardware configuration parameters of the phased array antenna (pre-stored in the digital signal processor) are called:

[0105] for The adjustable range of the pointing angle of a phased array antenna is determined by the hardware design (such as azimuth angle). Adjustable range is Pitch angle Adjustable range is ,like If the parameter exceeds this range, it is determined to be an invalid parameter, and a parameter correction request is immediately sent to the dynamic beam calculation unit 200.

[0106] for : Call the rated power range parameters of the power amplifier, if If the value is lower than the rated minimum or higher than the rated maximum, it is determined to be an invalid parameter, and a parameter correction request is triggered accordingly.

[0107] Only when and After all verifications pass, the process proceeds to the next instruction conversion step.

[0108] S310.2. Based on the element spacing and operating wavelength parameters of the phased array antenna, the actual beam pointing angle is determined. The phase difference requirement of each array element is converted into a digital phase control word containing the phase adjustment amount, and the digital phase control word corresponds one-to-one with the array element number.

[0109] Specifically, it calls the fixed parameters of the phased array antenna—the element spacing. (e.g. 0.5) ) and operating wavelength (Determined based on satellite communication frequency bands, such as Ka band) (Approximately 1cm), based on the correlation logic between the beam pointing of the phased array antenna and the phase difference of the array elements, will Converted to the phase difference requirements of each array element:

[0110] First The phase difference between adjacent elements is calculated based on the relationship that "the phase difference between the elements is proportional to the pointing angle, the spacing between the elements, and the operating wavelength".

[0111] Based on the calculated phase difference, a digital phase control word containing the phase adjustment amount of each array element is generated (using a binary encoding format, such as 16-bit encoding). Phase adjustment range), and the digital phase control word and the array element number are strictly one-to-one correspondence - the array element number is allocated according to the array element arrangement order of the phased array antenna (such as numbered 1, 2, 3...N from left to right and from top to bottom), to ensure that each array element can receive dedicated phase adjustment commands.

[0112] S310.3. Based on the gain curve parameters of the power amplifier, adjust the transmit power to match the parameters. This is converted into a power adjustment command, which includes a quantized value of the power amplification factor, and the quantized value is matched with the transmit power. They exhibit a linear mapping relationship.

[0113] Specifically, the gain curve parameters of the power amplifier are retrieved (pre-calibrated on the ground and stored in the hardware; the gain curve reflects the relationship between the input signal and the output power), and the transmit power is adjusted according to this curve. Convert to power amplification factor:

[0114] First determine The corresponding output power target value is then used to deduce the power amplification factor required by the power amplifier (amplification factor = output power target value / input signal power).

[0115] Convert the power amplification factor to a quantization value (e.g., 8-bit quantization, quantization range 0~255), and the quantization value is... A linear mapping relationship exists—that is For every fixed increase in value (e.g., 1W), the quantization value increases by a corresponding fixed value (e.g., 5), ultimately generating a power adjustment command containing that quantization value, ensuring the power amplifier can output accurately according to the command. The corresponding power.

[0116] In this embodiment, the beam adjustment unit 300 further includes a beam control module 320. The beam control module 320 implements beam control and resource scheduling based on the physical control commands output by the command parsing module 310, including the following steps:

[0117] S320.1 The digital phase control word output by the receiving command parsing module 310 applies a corresponding phase adjustment amount to each element of the phased array antenna through an adaptive phase optimization algorithm, so that the main lobe of the beam points to the actual beam pointing angle. ;

[0118] Specifically, it first receives the digital phase control word output by the instruction parsing module 310. ( , (Total number of array elements in the phased array antenna), processed by a digital signal processor Reverse decoding to the first Initial phase adjustment of each array element The decoding formula is ,in for The number of binary bits, for example: ,make sure The range is ;

[0119] Then, the adaptive phase optimization algorithm is run:

[0120] The first step is to acquire the actual pointing angle of the main lobe of the beam using the signal direction detection component at the antenna receiver. ,in For actual azimuth, (The actual elevation angle is in degrees); calculate the actual beam pointing angle relative to the target. The deviation is given by the formula: , ,in , These are the azimuth and elevation deviations, respectively, both in degrees.

[0121] The second step is to set the pointing accuracy threshold. (For example: ),like or Then calculate the phase fine-tuning amount. ,in For fine-tuning coefficients, This indicates taking the maximum deviation; and combining the deviation direction with... The final phase adjustment amount is obtained; where For symbolic functions, When the direction is right, add 1; otherwise, subtract 1 to ensure that the fine-tuning direction matches the deviation direction.

[0122] The third step will After applying to the corresponding array element, re-collect. And calculate the new deviation. ,like and The algorithm converges, and the main lobe of the beam is accurately pointed. Otherwise, repeat the above fine-tuning process.

[0123] Specifically, in this embodiment, the actual pointing angle of the main lobe of the beam can be realized through the signal direction detection component at the antenna receiver using the MUSIC (Multi-Signal Classification) algorithm based on array signal processing. The acquisition process specifically involves: constructing a covariance matrix using the received signals from the phased array antenna elements; performing eigenvalue decomposition on the covariance matrix; estimating the direction of arrival (DOA) of the signal by finding the orthogonality between the signal subspace and the noise subspace; and then determining the actual pointing angle of the beam main lobe. .

[0124] Understandably, low- and medium-Earth orbit satellites are characterized by their low orbital altitude (typically 500-2000 km) and high relative speed with ground user terminals. Simultaneously, phased array antenna elements have hardware manufacturing tolerances, and temperature changes during on-orbit operation can cause phase drift. These factors collectively lead to beam pointing deviations. Traditional open-loop phase control only applies phase adjustment according to preset commands, failing to detect actual pointing deviations, which accumulate over time with satellite motion. This algorithm, however, uses a closed-loop mechanism of "real-time acquisition of the actual beam main lobe pointing—calculation of the deviation from the target pointing—dynamic fine-tuning of array element phases" to directly address the core problem of "unpredictable and continuously expanding phase errors in dynamic scenarios, causing the beam main lobe to deviate from the user terminal coverage area," thus forming an adaptive correction capability.

[0125] Meanwhile, in low- and medium-Earth orbit (LEO) satellite communication scenarios, beam pointing accuracy directly determines whether the user terminal is in the high-gain region of the main lobe: if the pointing deviation is too large, it will lead to a decrease in the received signal strength and even communication link interruption. This algorithm, through real-time deviation detection and phase fine-tuning, can continuously lock the main lobe of the beam near the target pointing angle even under rapid satellite movement and dynamic changes in hardware parameters, ensuring that the user terminal is always within the main lobe coverage area and effectively avoiding communication quality fluctuations caused by pointing deviation. At the same time, since there is no need to excessively increase the transmission power to cover potentially biased areas, unnecessary power consumption can be reduced, improving onboard energy utilization efficiency. This closed-loop optimization mechanism designed for the dynamic characteristics of LEO is not a simple adoption of beam control methods for fixed ground scenarios, but a targeted solution formed by combining satellite motion laws and hardware characteristics.

[0126] S320.2 During beam pointing, the mutual interference signal of adjacent beams is collected through the antenna receiver. When the mutual interference signal strength exceeds the preset threshold, the phase compensation amount of the edge array elements is dynamically adjusted until the mutual interference signal strength drops below the threshold.

[0127] Specifically, the mutual coupling interference signal between adjacent beams is first acquired by the signal acquisition unit at the antenna receiver, and then converted into an electrical signal power. And through formula Calculate the strength of the interference signal ,in for The corresponding power reference value; then the preset interference intensity threshold is called. (For example: (to ensure that business signal transmission is not affected) No adjustment is needed; maintain the phase of the array elements. ;like Then calculate the phase compensation amount of the edge array elements (array elements closer to the interference source). ,in This is the initial compensation amount. To the maximum tolerable interference intensity, and Superimposed on the edge array elements ,get Finally, the interference signal strength was re-acquired. ,like Then repeat the compensation process until... And throughout the process, the direction of the main lobe is monitored in real time to ensure... No offset occurs.

[0128] S320.3 The power adjustment command output by the receiving command parsing module 310, combined with the user distribution spatial density transmitted by the satellite-ground coordination unit 400, adjusts the transmit power to the appropriate value. The power is allocated to each sub-beam within the coverage area according to density ratio, prioritizing the power needs of high-density user areas, thus completing the multi-beam power configuration.

[0129] Specifically, it first receives the power adjustment command (including the transmit power adaptation value) output by the command parsing module 310. (corresponding amplification factor quantization logic), and Classified as basic power With dynamic power allocation The division formula is as follows ( The base power ratio ensures that each sub-beam has basic communication capabilities. (This is for the dynamic allocation part); subsequently, the user distribution spatial density of each sub-beam within the coverage area is obtained through the satellite-ground coordination unit 400. ( , The total number of sub-beams, for example: , Units are ), calculate the first Density ratio of individual beams ,in To ensure total user density Next, calculate the first... The final power of the sub-beam ,in This is the amount of basic power distributed equally. To achieve dynamic power allocation, sub-beams in high-density regions obtain more dynamic power; finally, Substitute the power conversion logic of instruction parsing module 310 (i.e. , For input reference power, =2、 =5 represents the quantization coefficient and offset), generating power adjustment commands for each sub-beam and transmitting them to the power amplifier to complete multi-beam power configuration and achieve real-time resource scheduling.

[0130] The satellite-ground coordination unit 400 is used to establish a two-way data link between the satellite and the ground station, transmit the spatial density of user distribution and satellite payload operating status parameters, and support the updating of basic data for beam adjustment.

[0131] It is understood that in this embodiment, the satellite-ground coordination unit 400 uses the onboard data transmission hardware platform as a carrier (integrating a Ka-band transceiver, anti-interference signal processor, time synchronizer and data buffer unit). Its core function is to establish a two-way data link between the satellite and the ground station, transmit user distribution spatial density and satellite payload working status parameters, and provide basic data support for beam adjustment.

[0132] Core components and functions of the onboard data transmission hardware platform adapted for low and medium Earth orbit satellite communication scenarios:

[0133] Ka-band transceiver: As the core of the physical layer of the link, it supports uplink (ground station to satellite) and downlink (satellite to ground station) bidirectional communication. The operating frequency band conforms to the Ka-band range of medium and low orbit satellites allocated by the International Telecommunication Union (ITU). The transmission and reception channels are independently designed to ensure interference-free bidirectional data transmission.

[0134] Anti-interference signal processor: integrates frequency hopping spread spectrum baseband processing circuit, supports real-time generation of frequency hopping patterns and spreading codes, used to resist channel noise and human interference;

[0135] Time synchronizer: Based on satellite ephemeris and ground station GPS timestamps, it realizes time synchronization between satellite and ground station (synchronization error controlled within milliseconds) to ensure the timing consistency of data transmission;

[0136] Data caching component: Employs a spaceborne flash memory chip to temporarily store user distribution data to be transmitted and received payload calibration parameters, preventing data loss due to link interruption.

[0137] In this embodiment, the satellite-ground coordination unit 400 includes a bidirectional link management module 410 and a data synchronization module 420, wherein:

[0138] The bidirectional link management module 410 establishes an anti-interference communication link between the satellite and the ground station through the Ka band, uses frequency hopping spread spectrum technology to resist channel noise, and monitors the link bit error rate in real time. When the link bit error rate exceeds the preset threshold, a link reconnection mechanism is triggered.

[0139] Specifically, the bidirectional link management module 410, relying on the anti-interference signal processor and the Ka-band transceiver, establishes and maintains the anti-interference communication link according to a preset process:

[0140] During the link establishment phase, a link establishment request containing satellite identification code and orbital parameters is sent to the ground station via the Ka-band transceiver. After receiving the response signal from the ground station containing the ground station ID and frequency hopping parameters, the frequency hopping frequency set is extracted. With frequency hopping period The anti-interference signal processor generates a matching pseudo-random frequency hopping pattern to complete the link initialization;

[0141] In terms of anti-interference mechanisms, frequency hopping spread spectrum composite technology is adopted, each The communication frequency is switched according to the frequency hopping pattern to avoid continuous interference, and the signal frequency band is extended by spreading code (such as m sequence) to improve noise immunity.

[0142] In link maintenance, the link error rate is calculated by real-time statistics of the received data check bits. ,set up The normal threshold for the link, when Maintain the current parameters when When the link is reconnected, the new frequency hopping parameters are obtained by resending the request and the link is rebuilt to ensure communication continuity.

[0143] The data synchronization module 420 transmits user distribution spatial density data to the beam demand sensing unit 100 at a preset cycle, including the number of user terminals and service types in different latitude and longitude grids; it also receives satellite payload calibration parameters sent by the ground station and updates operating status parameters (such as satellite antenna gain, power amplifier efficiency, etc.) to provide a real-time payload performance benchmark for the dynamic beam calculation unit 200.

[0144] Specifically, the data synchronization module 420, relying on a time synchronizer and a data caching component, completes bidirectional data synchronization according to a preset cycle:

[0145] Regarding user-distributed spatial density data transmission, by period (Based on user mobility characteristics) Data is transmitted to the beam demand sensing unit 100, and the data is in the form of... The grid is based on latitude and longitude and includes a unique grid identifier. Number of active user terminals within the grid and main business types Before transmission, the data is checked and encoded using a CRC checksum. After transmission, it is temporarily stored in the data buffer unit until the data is received and confirmed.

[0146] Regarding the synchronization of satellite payload calibration parameters, it is done periodically. (Based on load parameter stability settings) Receive calibration parameters sent by the ground station, including antenna gain correction coefficients. Power amplifier efficiency and beam pointing deviation compensation value Upon receiving the data, the parameters are updated in real time to the parameter register of the dynamic beam calculation unit 200, and the old parameters are archived in the data cache unit to retain the most recent three historical data.

[0147] In coordination with other units, the satellite-to-ground coordination unit 400 transmits data to the beam demand sensing unit 100. , , It provides the basic input for generating user terminal motion parameters; and synchronizes with the dynamic beamforming unit 200. , , Used to correct deviations in beam theory parameter calculations; simultaneously, link status information (such as current status) is also included. The value is shared with the beam adjustment unit 300 to assist it in adjusting the power allocation strategy when the link quality is poor, so as to ensure the data closed loop and functional coordination of the entire dynamic beam adjustment system.

[0148] In addition, the ground station for " When counting the number of users within the grid, a fusion method of "user terminal location reporting + satellite payload beam scanning detection" is adopted:

[0149] On the one hand, user terminals obtain their own location information based on satellite navigation systems (such as GPS and BeiDou) and periodically report it to the ground station via uplink signaling;

[0150] On the other hand, the satellite payload's multi-beam antenna scans the coverage area at a preset period, receiving downlink pilot signals from user terminals to assist in verifying and supplementing user location distribution data. Simultaneously, it clarifies the spatial density of user distribution. The accuracy of the acquisition is such that the statistical error of the number of users within the grid does not exceed 5%, in order to ensure the reliability of the power allocation logic.

[0151] The performance monitoring unit 500 is used to detect the actual coverage parameters of the beam and feed the monitoring data back to the dynamic beam calculation unit 200 and the beam execution adjustment unit 300.

[0152] Understandably, the performance monitoring unit 500 uses the onboard monitoring hardware platform as its core carrier. This platform integrates a beacon receiver, signal processing components, and a high-speed data transmission interface. It can collect the actual beam coverage parameters in real time and feed the monitoring data back to the dynamic beam calculation unit 200 and the beam execution adjustment unit 300 through the onboard data bus, providing a basis for closed-loop optimization of beam parameters.

[0153] In this embodiment, the performance monitoring unit 500 includes a coverage parameter acquisition module 510 and a feedback control module 520, wherein:

[0154] The coverage parameter acquisition module 510 acquires the signal strength distribution, 3dB beamwidth, and edge roll-off rate of the actual beam coverage area through the beacon receiver in the satellite payload, while simultaneously recording the actual measured value of the beam pointing angle. Compared with theoretical value deviation ;

[0155] Specifically, the coverage parameter acquisition module 510, relying on the onboard beacon receiver and signal processing components, acquires the core parameters of the actual beam coverage:

[0156] The beacon receiver receives signals from preset beacon nodes (or beacon signals actively fed back by user terminals) within the beam coverage area. Through multi-channel synchronous sampling technology, it acquires signal strength data at different spatial locations within the coverage area and forms a signal strength distribution map.

[0157] Based on this spectrum, the 3dB beamwidth (i.e. the angle range corresponding to when the signal strength drops to the peak value of 3dB) is determined by peak detection and interval calculation of the signal processing component.

[0158] Simultaneously, the signal strength variation trend with angle in the edge region (near the edge of beam coverage) is analyzed, and the edge roll-off rate (the change in signal strength per unit angle) is calculated. For the beam pointing angle, the beacon receiver obtains the actual measured value of the beam pointing angle using signal angle of arrival measurement technology. and the theoretical value output by the dynamic beam calculation unit 200. By comparison, the pointing angle deviation was calculated. , All collected data is temporarily stored in the buffer of the signal processing component, waiting for the feedback control module 520 to call it.

[0159] The feedback control module 520 feeds back the signal strength distribution and beamwidth data to the dynamic beam calculation unit 200 to optimize the transmit power adaptation value. The calculation model; and the pointing angle deviation Feedback is sent to the beam control unit 300 as a correction value for the phase control word to achieve closed-loop control.

[0160] Specifically, the feedback control module 520 includes a high-speed data transmission interface that logically feeds back the collected coverage parameters to the corresponding units:

[0161] For the dynamic beamforming unit 200, the feedback control module 520 transmits the signal strength distribution and 3dB beamwidth data to the basic parameter calculation module 210 of the dynamic beamforming unit 200. The dynamic beamforming unit 200 then adjusts the transmit power adaptation value based on the difference between the actual signal strength distribution and the theoretical coverage requirements. The parameters in the calculation model (such as adjusting the proportion of power reserve margin according to the signal strength at the actual coverage edge) make the transmit power more accurately match the actual coverage scenario.

[0162] For the beam adjustment unit 300, the feedback control module 520 will adjust the pointing angle deviation. The instruction parsing module 310, which transmits the data to this unit, will generate the digital phase control word. As a phase correction factor, it is incorporated into the phase difference calculation of the array elements, and the phase control word of each array element of the phased array antenna is adjusted to correct the beam pointing, thereby realizing closed-loop control of the beam pointing and ensuring that the actual beam pointing is closer to the theoretical value.

[0163] Through the above design, the performance monitoring unit 500 can fully collect the actual beam coverage parameters and form effective feedback, so that the transmit power calculation of the dynamic beam calculation unit 200 and the beam pointing control of the beam execution adjustment unit 300 can be optimized based on the actual coverage, ensuring the closed-loop reliability of the entire beam adjustment system.

[0164] Those skilled in the art will understand that the process of implementing all or part of the steps of the above embodiments can be carried out by hardware or by a program instructing the relevant hardware.

[0165] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A dynamic beam adjustment system for low- and medium-Earth orbit satellite communication, characterized in that, Comprise: Beam demand perception unit (100), the beam demand perception unit (100) is used to gather the basic physical parameters including user terminal side parameter and satellite side parameter in the coverage range of low-orbit satellite; Dynamic beam calculation unit (200), the dynamic beam calculation unit (200) is based on the basic physical parameters of beam demand perception unit (100), and the relative motion relation of satellite and user is combined to calculate beam core parameter, including beam pointing angle, transmission power adaptation value, and the influence of complex environment on beam coverage is offset through multi-factor collaborative compensation mechanism;The multi-factor collaborative compensation mechanism realizes dynamic correction of pointing angle through the weighted coupling of satellite motion compensation, user movement compensation and atmospheric refraction correction, and the compensation weight of satellite motion compensation, user movement compensation and atmospheric refraction correction is adjusted in real time according to communication scene; Beam execution adjustment unit (300), the beam execution adjustment unit (300) is used to convert the beam core parameter output by dynamic beam calculation unit (200) into physical control instruction, realizes beam accurate pointing and interference suppression through adaptive phase optimization algorithm, and completes multi-beam power configuration based on the transmission power adaptation value output by dynamic beam calculation unit (200), realizes resource real-time scheduling; Star-ground coordination unit (400), the star-ground coordination unit (400) is used to establish the bidirectional data link of satellite and ground station, and transmit the spatial density of user distribution and satellite load working state parameter, support the basic data update of beam adjustment; Performance monitoring unit (500), the performance monitoring unit (500) is used to detect the actual coverage parameter of beam, and feedback monitoring data to dynamic beam calculation unit (200) and beam execution adjustment unit (300).

2. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 1, wherein, The beam demand perception unit (100) comprises user parameter perception module (110) and satellite parameter perception module (120), wherein: The user parameter perception module (110) is used to receive the uplink signaling and probe signal transmitted by user terminal, and gather user terminal side parameter including real-time spatial coordinates, motion speed, service signal bandwidth and communication link signal-to-noise ratio; The satellite parameter perception module (120) is based on satellite-borne navigation receiver and load state sensor, and gathers satellite side parameter including satellite orbit position, motion velocity vector and elevation angle.

3. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 2, wherein, The beam demand perception unit (100) further comprises data preprocessing module (130), and the data preprocessing module (130) is used to process the basic physical parameters collected by user parameter perception module (110) and satellite parameter perception module (120), specifically including: The real-time spatial coordinates of user terminal collected by user parameter perception module (110) and the satellite orbit position collected by satellite parameter perception module (120) are converted into three-dimensional coordinates in WGS84 geodetic coordinate system through coordinate system conversion; Abnormal value identification is performed on the collected user terminal side parameters and satellite side parameters, and when the user terminal movement speed exceeds the normal moving range of the ground terminal and the satellite elevation angle is lower than the effective communication elevation angle threshold of the medium-low orbit satellite, the abnormal data is marked and the re-collection process is triggered; Synchronization time stamps are added to the verified user terminal side parameters and satellite side parameters.

4. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 3, wherein, The dynamic beam calculation unit (200) comprises a basic parameter calculation module (210) configured to calculate a theoretical value of a beam core parameter based on a basic physical parameter of the beam demand perception unit (100), and specifically comprises: Based on the real-time spatial coordinates of the user terminal and the orbital position of the satellite, a beam theoretical pointing angle is calculated through spherical geometry, the beam theoretical pointing angle including a theoretical azimuth angle and a theoretical elevation angle ; Based on the straight-line distance between the user terminal and the satellite , the communication link signal-to-noise ratio , and the traffic signal bandwidth , the initial transmit power value , is calculated as a reference quantity for the transmit power adaptation value.

5. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 4, wherein, The dynamic beam calculation unit (200) further comprises a multi-factor compensation module (220) configured to calculate each compensation component of the pointing angle, and specifically comprises: Based on the beam requirement sensing unit (100) collected satellite tangential velocity The straight line distance between the user terminal and the satellite , calculate the signal propagation delay , combined with , And Determine the satellite motion compensation amount ; Based on the beam requirement sensing unit (100) collected user terminal motion speed Distance from straight line , combined with signal propagation delay , determine the user movement compensation amount ; Based on the beam requirement perception unit (100) collected satellite elevation angle , introduce atmospheric refraction correction coefficient , determine the atmospheric refraction correction amount .

6. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 5, wherein, The dynamic beam calculation unit (200) further comprises a weight synthesis module (230) configured to dynamically adjust the compensation weight based on the communication scenario and synthesize the final parameter, comprising the following steps: S230.1, acquiring satellite elevation angle collected by the beam demand awareness unit (100) , user terminal motion speed and communication link signal-to-noise ratio , and determining the current communication scenario based on the satellite elevation angle , user terminal motion speed and communication link signal-to-noise ratio ​ S230.2, for the communication scenario of the decision, the corresponding weight coefficients are configured respectively for satellite motion compensation, user movement compensation, and atmospheric refraction correction , and ; S230.3, receiving the satellite motion compensation quantity output by the multi-factor compensation module (220) , the user movement compensation quantity , the atmospheric refraction correction quantity , and synthesizing the total compensation quantity according to the weight coefficient ;​ S230.4, Call the theoretical azimuth angle output by the basic parameter calculation module (210). Compared with theoretical pitch angle Combined with the total compensation amount Make corrections to obtain the actual beam pointing angle. ; S230.5, calling the initial transmission power value output by the base parameter calculation module (210) , based on the total compensation amount , adjusting to generate a transmission power adaptation value .

7. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 6, wherein, The beam execution adjustment unit (300) comprises an instruction analysis module (310) configured to convert the beam core parameter into a physical control instruction, comprising the following steps: S310.1、receive the actual beam pointing angle output by the dynamic beam calculation unit (200) adaptation value verify the validity of the parameters, ensure in the pointing angle adjustable range of the phased array antenna, in the rated power interval of the power amplifier; S310.2, based on the inter-element spacing of the phased array antenna and the working wavelength parameters, the actual beam pointing angle converts into the phase difference requirement of each element, generates a digital phase control word containing a phase adjustment amount, and the digital phase control word is one-to-one corresponding to the element number; S310.3, according to the gain curve parameters of the power amplifier, the transmit power adaptation value is converted into a power adjustment instruction, the power adjustment instruction includes a quantized value of a power amplification coefficient, and the quantized value and the transmit power adaptation value are in a linear mapping relationship.

8. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 7, wherein, The beam execution adjustment unit (300) further comprises a beam control module (320) configured to realize beam control and resource scheduling based on the physical control instruction output by the instruction analysis module (310), comprising the following steps: S320.1, receiving the digital phase control word output by the instruction analysis module (310), applying a corresponding phase adjustment amount to each element of the phased array antenna through an adaptive phase optimization algorithm, so that the main lobe of the beam points to the actual beam pointing angle ; S320.2, in the beam pointing process, the mutual coupling interference signal of the adjacent beam is collected through the antenna receiving end, and when the mutual coupling interference signal strength exceeds the preset threshold, the phase compensation amount of the edge element is dynamically adjusted until the mutual coupling interference signal strength decreases to below the threshold; S320.3, receiving the power adjustment instruction output by the instruction analysis module (310), combining the user distribution spatial density transmitted by the satellite-ground cooperative unit (400), and adjusting the transmission power value According to the density proportion, the power is distributed to each sub-beam in the coverage area, the power demand of the high-density user area is preferentially met, and the multi-beam power configuration is completed.

9. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 8, wherein, The satellite-ground cooperative unit (400) comprises a bidirectional link management module (410) and a data synchronization module (420), wherein: The bidirectional link management module (410) establishes an anti-jamming communication link between the satellite and the ground station through the Ka frequency band, uses frequency hopping spread spectrum technology to resist channel noise, and simultaneously monitors the link error rate in real time, and triggers the link reconnection mechanism when the link error rate exceeds the preset threshold; The data synchronization module (420) transmits user distribution spatial density data to the beam demand perception unit (100) at a preset period, including the number of user terminals and the type of service in different latitude and longitude grids; synchronously receives the satellite payload calibration parameters sent by the ground station, updates the working state parameters, and provides a real-time payload performance benchmark for the dynamic beam calculation unit (200).

10. The dynamic beam adjustment system for low and medium earth orbit satellite communication of claim 9, wherein, The performance monitoring unit (500) comprises a coverage parameter collection module (510) and a feedback control module (520), wherein: The coverage parameter acquisition module (510) acquires the signal strength distribution, 3dB beam width and edge roll-off rate of the actual coverage area of the beam through a beacon receiver in the satellite payload, and records the actual measurement value of the beam pointing angle at the same time deviation from the theoretical value of the beam pointing angle ; The feedback control module (520) feeds back the signal strength distribution and beamwidth data to the dynamic beam calculation unit (200) to optimize the transmit power adaptation value. The calculation model; and the pointing angle deviation Feedback is sent to the beam control unit (300) as a correction value for the phase control word to achieve closed-loop control.

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